Downloaded from j INCH-POUND~ …

j INCH-POUND~MI L-D-8708C(AS)12 Auaust 1991SUPERSEDINGMI L-D-8708 B(AS)31 January 1969

I

MILITARY SPECIFICATION

DEMONSTRATION : AIRCRAFT WEAPON SYSTEMS ,GENERAL SPECIFICATION FOR

Thts specification IS approved for use by the Naval A!r SystemsCommand, Department of the Navy, and 1s available for use by al 1Departments and Agencies of the Department of Defense.

1. SCOPE

1.1 *. This specif I cation establishes the general requirementsfor demonstration of Naval aircraft weapon systems during ful 1 scaleengineering development. The general requirements may be modlffed andamplified by an addendum to this specification for specific weaponssystems. “Demonstration” refers to al 1 contractor tests and evaluationsconducted during full scale development including efforts associated withperforming and reporting on the tests required by this specification.

1.2 PurDose. This specification defines the tests required forcontractor demonstration of Naval aircraft prior to the final phase ofDT-11 (TECHEVAL) .

1.3 ~ lit . The requirements of this specifi cation apply toall new aircraft weapon systems or to major modification or significantalteration to an existing system.

?.4 Afl! hi i Addenda shal 1 agree with thisspecification in paragraph arrangement: numbering, and headings, exceptwhere a paragraph is 1 i steal i n the addendum as “not appl i cable” or “notrequi red, ” subsequent subparagraphs wi 11 be omitted. If the numberingsequence is not affected, subparagraphs may be added as required. Incases of discrepancies between this specification and the addenda, theaddenda shal 1 govern.

1.5 Deviatio ns. The approval of analyses, test plans, procedures,or test reports which incorporate variations from the stated requirementsdoes not constitute approval of a deviation. Deviations from therequirements of this specification, its addenda, or the detailspecification may be granted only by the contracting activity in writing.

Beneficial comments (recommendations, additions, deletions) and anypertinent data which may be of use in improving this document should beaddressed to: Naval Air Engineering Center, Systems Engineering andStandardization Department (SESD) Code 53, Lakehurst, NJ 08733-5100, byusing the Standardization Document Improvement Proposal (DD Form 1426)

~c hi ument or v letter.

AMSC NIA

DISTRIBUTION STATEMENT A. Approved for public release; di str

FSC 1510

bution is unlimited.

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MIL-D-8708C(AS)

2. APPLICABLE 00CUMENTS

2.1 Government documents.

2:1 .1-. Specifications. standards. and handbooks. The following specifications,standards, and handbooks form a part of this document to the extent specifiedherein. Unless otherwise soecified. the issues of these documents. are thoselisted in the issue ofStandards (DOOISS) and

SPECIFICATIONS

MILITARY

MI L-E-5007

MI L-B-50B7

MI L-k&508BMI L-F-5372MI L-E-5400

MI L-T-5522

MI L-C-5809

MI L-T-5842

MI L-E-6051

MI L-I-6115

MI L-D-6728MI L-W-6729

MI L-L-6730

MI L-E-7016

MI L- E-70B0

MI L-C-7762MI L-F-7872

MI L-G-7940

MI L-S-B512

MI L-B-B565

the Department of Oefense Index of Specifi cations andsupplement thereto, cited in the solicitation (see 6.2).

Engines, Aircraft, Turbojet and Turbofan,General Specification forBonding, Electrical , and LightningProtection, for Aerospace SystemsHiring, Aerospace VehicleFuse, Current Limiter Type, AircraftElectronic Equipment, Aerospace GeneralSpecifi cation forTest Requirements and Methods for AircraftHydraulic and Emergency Pneumatic SystemsCircuit Breakers, Tri p-Free, Aircraft,General Specification forTransparent Areas on Aircraft Surfaces (Wind-shields and Canopies), Rain Removing andWashing Systems for, Oe-frosti ng, De-icing,Defogging, General Specification forElectromagnetic Compatibility Requirements,SystemInstrument System, Pitot Tube and FlushStatic Port Operated, Installation ofOampers, Engine Exhaust Flame and GlareHatertightness of Aircraft, Testing, GeneralSpecification forLighting Equipment; Exterior, Aircraft(General Requirements for)Electric Load and Power Source Capacity,Aircraft, Analysis ofElectrical Equipment, Aircraft, Selection andInstallation ofCompass, Installation ofFire and Overheat Warning Systems,Continuous, Aircraft, Test and InstallationofGages, Liquid Quantity, Capacitor Type,Installation and Calibration ofSupport Equipment, Aeronautical, Special,General Specification for the Oesign of

Battery Storage, Aircraft GeneralSpecification for

2


MI L-D-8708C(AS)

MI L-A-8591

MI L-I-8670.,-.

MI L-I-8671

MIL-I-8675MI L-C-8678

MI L-D-8683

MI L-1-8700

MIL-F-8785MI L-A-8860

MI L-A-8861MI L-A-8863

MI L-A-8867MI L-A-8868

MI L-A-8870

MI L-F-9490

MIL-F-15160MIL-F-)7874

MI L-C-18244

MI L-L-18276MI L-H-18325

MI L-S-18471

MI L-T-18606

MI L-T-1 8607

MIL-A-18717MI L-E-18927

MI L-D-19326

MI L-A-19736MI L-L-22589

Airborne Stores, Suspension Equipment andAircraft Store Interface (Carriage Phase),General Design Criteria forInstallation of Fixed Guns and AssociatedEquipment in Naval AircraftInstallation of Droppable Stores andAssociated Release SystemsInstallations, Aircraft ArmorCool 1 ng Requirements of Power PlantInstallationsDesign and Installation of Gaseous OxygenSystems in Aircraft, General SpecificationforInstallation and Test of Electronic Equipmentin Aircraft, General Specification forFlying Qualities of Piloted AirplanesAirplane Strength and Rigidity GeneralSpecification forAirplane Strength and Rigidity Flight LoadsAirplane Strength and Rigidity Ground Loadsfor Navy Acquired AirplanesAirplane Strength and Rigidity Ground TestsAirplane Strength and Rlgldity, Dataand ReportsAirplane Strength and Rigidity Vibration,Flutter, and Divergence - -Flight Control Systems, Destgn, Installation,and Test of P!loted Aircraft, (GeneralSpecification for)Fuses; Instrument, Power, and TelephoneFuel Systems, Aircraft, Installationand Test ofControl and Stabi 1 ization Systems:Automatic, Piloted Aircraft, GeneralSpecification forLighting, Aircraft Interior, Installation ofHeating and Ventilating Systems, Aircraft,General Specification forSystem, Aircrew Automated Escape, EjectionSeat Type, General Specification forTest Procedures for Aircraft EnvironmentalSys ternsThermal Anti-Icing Systems, Wing andEmpennageArresting Hook Installations, AircraftEnvironmental Control Systems, Aircraft,General Requirements forOesign and Installation of Liquid OxygenSystems in Aircraft, General SpecificationforAir Refueling Systems, General SpecificationLaunching System, Nose Gear Type, Aircraft for

3


MI L-D-8708 C(AS)

MIL-F-23447

NIL-R-23761

.,-.

MI L-C-23866MI L-E-24021MI L-H-25140

MI L-P-26292

MI L-P-26366

MI L-T-81571

MI L-8-81757

MI L-E-8191O

MI L-C-83413

MI L-8-83769

00D-C-85050

MI L-I-85071

MIL-B-85110

MI L-D-85520

MI L-E-85583

DOD-B-85584MI L-L-85762

STANDAROS

MILITARY

MI L-STD-454

MI L-STD-461

MI L-STD-470

MI L-STD-471

MI L-STD-704MI L-STD-785

Fire 14arning Systems, Aircraft, RadiationSensing Type, Test and Installation ofRegulator, Voltage and Control Panels,Aircraft, Direct Current Generator, GeneralSpecification forControl Set, Approach Power AN/ASN-54(V)Electrical Power Monitors, External, AircraftWeight and 8alance Control System (forAircraft and Rotorcraft)Pi tot and Static Pressure Systems,Installation and Inspection ofPropel ler Systems, Aircraft, GeneralSpecification forThermal Protective System, Al rcraft Cockpit,General Specification forBatteries and Cel 1s, Storage, Nickel-Cadmium,Aircraft, General Specification forElectrical Power Generating and ControlEquipment, Aircraft, General SpecificationsforConnectors and Assemblies, Electrical,Aircraft Grounding, General Specification for8atteries, Storage, Lead-Acid, GeneralSpecification forChargers, 8attery, Nickel-Cadmium, Aircraft,General Specification forInverters, Aircraft, DC to AC, GeneralSpecification for8ar, Repeatable, Release Holdback, AircraftLaunching, General Design Requirements forDesign and Instal latlon of On Board OxygenGenerating Systems in Aircraft, GeneralSpecification forElectric Power Generating Channel, VariableInput Speed, Alternating Current, 400 Hz,Aircraft; General Specification forBattery, Relay Control Unit, Al rcraftLighting, Aircraft, Interior, Night VisionImaging System (NVIS) Compatible

Standard General Reaui rements for ElectronicEqu~pmentElectromaqnet{c Emission and sUSCC?Dtibi 1 ityRequlreme~ts for the Control of ElectromagfieticInterferenceMaintainabi 1 ity Program Requirements forSystems and EquipmentsMaintainability Verification/Demons tration/EvaluationAircraft Electric Power CharacteristicsRel iabi 1 i ty Program for Systems and EquipmentDevelopment and Production

4


MI L-D-8708 C(AS)

MIL-STD-81O

MI L-STD-877

M1L~STD=882MI L-STD-1333

MI L-STD-l 385

MI L-STD-1388-1MI L-STD-1472

MI L-STD-l 757

MI L-STD-l 760

MI L-STD-1795

MI L-STD-2 165

DOD-STD-2 167DOD-STD-2169

MS90298

HAND800KS

MILITARY

MIL-HDBK-235-2

Environmental Test Methods and EngineeringGuidelinesAntenna Subsystems, Airborne Criteria forDesign and Location forSystem Safety Program RequirementsAircrew Station Geometry for Mi 1 ItaryAircraftPreclusion of Ordnance Hazards i n Electro-magnetic Fields, General Requirements forLogistic Support AnalysisHuman Engineering Design Crfteria forMilitary Systems, Equipment and FacilitiesLightning Qualification Test Techniques andAerospace Vehicles and HardwareAircraft/Store Electrical InterconnectionSystemLightning Protection of Aerospace Vehiclesand HardwareTestabi 1 ity Program for Electronic Systemsand EquipmentsDefense System Software DevelopmentHigh Altitude Electromagnetic PulseEnvironmentConnector, Receptacle, Electric Grounding

Electromagnetic (Radiated) Environment Consi-derations for Design and Procurement ofElectrical and Electronic Equipment,Subsystems and Systems, Part 2

(Unless otherwise indicated, copies of federal and militaryspecifications, standards, handbooks and bul let ins are available from theStandardization Documents Order Desk, 8ui lding 4D, 700 Robbins Avenue.Philadelphia, PA 19111 -5094.)

2.1.2fol lowing other Government docum!nts,part of this document to the extent specified herein. Unless otherwisespecified, the issues are those cited in the solicitation.

PUBLICATIONS

AR-40 Al 1 Weather Carrier Landing System AirborneSubsystem, General Requirements for

IRIG-STD-106 Range Commanders Counci 1 Telemetry StandardsOPNAVINST 3070.1 Operations SecurityNAVAIRINST 3710.1 Contractor’s Flight OperationsNAVAIRINST 3710.9 Anthropometric Accommodation in Naval

At rcraftOPNAVINST 4790.2 Naval Aviation Maintenance Program (NAMP)

Concepts, Objectives, Policies,Organizations, and Responsibilities

NAVAIRINST 13034.1 Flight Clearance Policies

5


MI L-D-8708C(AS)

(Copies of AR-40 are available from the Naval Al r Systems, StandardizationSection (Code AIR-511 Z2E), klashington, D.C. 20361-5110. Copies of NAVAIRINSTare avai lable from the Naval Air Systems Command, Forms (Code AIR-71233),Washington, D.C. 20361-7120. Copies of OPNAVINST are aval lable from the Chiefof Naval Operations, Washington, D.C. 20350. Copies of IRIG-STD are availablefrom the Secretariat, Range Commander’s Counci 1, U.S. Army White Sands MissileRange, New Mexico 88002. Copies of NAVAIRINST and OPNAVINST are also availablefrom the Naval Publications and Forms Center, (Code 1051 ), 5801 Tabor Avenue,Philadelphia, PA 19120-5099. )

2.2 Non-Government Dub licati~ The following document forms apart of this document to the extent ~pecif i ed herein. Unless otherwisespecified, the issues of the documents which are DoO adopted are thoselisted in the issue of the 00DISS cited in the solicitation. Unlessotherwi se specified, the issues of documents not 1 isted in the 0001SS arethe issues of the documents cited In the solicitation (see 6.2).

AMERICAN NATIONAL STANDAROS INSTITUTE (ANSI)

ANSI 239.18 Scientific and Technical Reports - Organiza-tion, Preparation and Production

(Application for copies should be addressed to the American NationalStandards Institute, 1430 8roadway, New York. NY 10018. )

(Non-Government standards and other publications are normal ly availablefrom the organizations that prepare or distribute the documents. Thesedocuments also may be available in or through 1 ibraries or other informationalservice s.)

2.3 Qrde of precedence In the event of a conf 1 ict between thetext of this ~ocument and the references cited herein, the text of thisdocument takes precedence. Nothing in this document, however, supersedesapplicable laws and regulations unless a specific exemption has beenobtained.

2.4 Streaml ininq. This document has been streamlined. ADDendix C toMI L-D-8708 1 i sts those documents requi red for acquisition and is apart of MI L-D-8708. Those documents 1 i steal in appendix C have theas those referenced directly in MI L-O-8708 (first tier documents).documents, referenced through tiering, may be used as guidance andto supplement MI L-D-8708. MI L-D-8708 is a streamlined document.

3. REQUIREMENTS

mandatorysame status

Al 1 otherinformation

3.1 Proa am Dlannina info matio Before demonstrations begin, programplanning info~mation required ~y thenContract Data Requirements List (CORL)shal 1 have been submitted and approved by the acqui ring activity.

3.1.1 Sccme a d con rrelat i ve Drovision$.

3.1 .1.1 Location of demonst ation Droa amdemonstration program shal 1 be a; defined i: thePlan.

6

The location for theDemonstration Program


MI L-D-8708 C(AS)

3.1.2 Plannlna confere ces Conferences shal 1 befaci 1 itate accompl t shment o; the various categories ofConferences WI 11 be convened by the acauirlna actlvlt~

conducted todemonstrations.uDon notification

by. the contractor that he is p~epared to pre~ent the ~ata or i nformat ionrequl Ted for the specific conference. The conference site wi 11 beselected by the acquiring activity. The time when the conference shal 1be scheduled Is presented In Tables VIII and IX (see Appendix B).

3.1.2.1 Instrum&ation Dlan Ina con feren~ A conference sha 11 beheld not later than 18 months prl~r to the scheduled release of the firstaircraft for flight. Participants will )nclude representatives of thecontractor, the cognizant Test Authority, and the acquiring actlvi ty. Atthe time of the conference, the contractor shal 1 have prepareddemonstratlon lnstrumentatlon data sufficiently complete to indicate theneed for the instrumentation in fulfi 11 ing the demonstrationrequirements. The data shall include:

a. A funct~onal block diagram and detailed description of theproposed instrumentation system. This shal 1 include samplerates, tape recorder speeds, telemetry bandwidth requirements,and unique instrumentation requirements.

b. A complete 1 i st of variables to be measured with each demon-stration aircraft and the expected overal 1 accuracy and frequencyresponse of each measured variable.

c. A complete 1 i st of contractor-furni shed special f 1 ight testinstrumentation and proposed Gove rnment-f urni shedinstrumentation. This list shall completely identify thepurpose, intended function, location, and requ~red responsecharacteristics of the instrumentation.

3.1.2.2 Structural con ferences.

3.1.2 .2.1 .Structura 1 Ins trumentat ion DlaJM na conferences.i Astructural lnstrumentation conference shal 1 be held not later than twomonths prior to lnltlatlon of the flight load calibration test or thefl Ight loads survey, whichever occurs first. If necessary, a secondstructural instrumentation conference shal 1 be held In conjunction withthe Structural F1 ight Load Survey Plannlng Conference.

3.1 .2.2.2 Structural fl iaht load sur ev Dlannl~ conference.v Onemonth after submittal of the structural bui Idup data In the DemonstrationPlanning and Progress Report and prior to initiation of the flight loadssurvey, a conference shal 1 be held to define the fl lght test plan for theloads survey.

3.1 .2.2.3 St uctural fl laht demo stratlon Dlann na confere C?i Atleast one month &ior to the structur~l demonstration tests of +abie IC aconference shal 1“ be held to final Ize the aircraft configuration, testprocedures, and the instrumentation to be used in the demonstration. Thecontractor shal 1 present substantiating data to support selection of thecritical demonstration parameters for the major structural components.Summary data of the f 1 ight load survey results and structural f 1 ightlimitation tests shall be included. The results of this conference shallbe confirmed by submittal of a summary report.

7


MI L-D-8708C(AS)

3.1 .2.2.4 Structural a’round loads and carrier suitabi 1 i tydemonstration Dlanninq conference. At least six months prior to land-based takeoff, landing, and taxi tests for land and carrier-basedaircraft or carrier suitability tests, a conference shall be held tofinalize the aircraft configuration, test procedures, and instrumentationto be used in the demonstration. The results of this conference shall beconfirmed by submittal of a summary report.

3.1 .2.2.5 Structural dwiamic fliqht demonstration Dlanninqco nference. At least one month prior to the structural dynamic flightdemonstration tests, a conference shal 1 be held to finalize thestructural dynamic flight test program. Upon completion of eachaeroelastic stability flight test phase, additional conferences shal 1 beheld to revieu the test results, determine if any deficiencies must becorrected prior to commencing the next aeroelastic stabi 1 ity flight testphase, and establish the maximum permissible flight speed envelope. Theminutes of this conference shal 1 be confirmed by submittal of a summaryreport.

3.1 .2.3 Aerodvnami c conferences.

3.1 .2.3.1 Performance data-reduction Procedures conference. Atleast six months prior to the performance demonstration tests, aconference shall be held to discuss the procedures and methods to be usedfor reduction of the performance demonstration data.

3.1 .2.3.2 Hirsh Anale Of Attack (AOA) and soin Dlanninq conferences.No later than one month prior to initiation of the high AOA and spin builduptests, a conference shall be held to establish critical flight conditions tobe investigated. Upon completion of buildup spin tests, another conferenceshall be held to review the results of the buildup tests, and toredefine, as necessary, the tests to be formal ly demonstrated.

3.1 .2.3.3 Performance demonstration Dlannina conferences. Aconference shal 1 be held at least four months prior to the fuelconsumption tests to review Dreliminarv test data and establish the datapresentation format and data” reduction-procedures to be used in preparingthe guaranteed performance report.

3.1 .2.3.4 Flvina aualities demonstration conference. Not later thanone month before the start of the formal flying qual i ties demonstrationtests, a conference shall be held to discuss all relevant itemspertaining to the demonstration.

3.1 .2.4 Avionics demonstration co nference. Not later than sixmonths prior to the scheduled date for the avionics demonstration: aconference shall be held to establish test periods and sites required toperform the demonstration.

3.1.3 ODerations Securitv (OPSEC) . The contractor shall comply withthe OPSEC security measures of OPNAVINST 3070.1. This applies

I particularly to telemetry and automatic data processing.

I

3.1.4 Fliciht monitDrinq.

8


MI L-L)-8708C(AS)

3.1 .4.1 Motion Dicture ca era or video taDe co craw Mot ionpicture camera or video tape c!verage shal 1 be obtained o; first f 1 ightsand other significant development flight tests.

-= 3:1. 4.2 1~ vera . Telemetry and instrumentation recordingsystem coverage shal 1 be provided as specified at the instrumentationplanning conference. Real-time recording and observation of criticalparameters shal 1 be provided. Telemetry shal 1 be required for al 1demonstration flights. The use of telemetry on other than demonstrationf 1 ights shal 1 be mutually agreed on by the contractor and the TestAuthority. At the instrumentation planning conference, and prior toprocurement and installation of telemetry and Instrument recordingsystems, the following shal 1 be determined:

a. Compatlbi 1 ity of proposed telemetry equipment and instrumentrecording systems with IRIG Standard 106 and ground equipment atal 1 proposed test and demonstration locations.

b. Incorporation of a backup source of power to ensure continuity ofpower for data acquisition in the event of primary power fai lure.

c. The extent to which telemetry coverage WI 11 be employed duringdemonstration flights witnessed by Test Authorities.

d. Data security measures.

3.1.4.3 ~. During initial flights at thecontractor’s plant, takeoffs and landings shal 1 be witnessed by both thecontractor and representatives of the Test Authority. Abnormal flightcharacteristics shall be recorded.

3.1 .4.4 chase aircraft. Chase aircraft shall be used for the firstflight of each aircraft outside the confines of the airfield. For otherflights, at or near the contractor’s plant or at Government facilities,determination of whether chase aircraft are to be used shal 1 be made bythe cognizant Test Authority.

3.1.5 Instrumentation.

3.1.5.1 ~- Maximum utilization shall be made oftest lnstrumentation available from the Special Flight Test InstrumentatlonPool (SFTIP) at NAVAIRTESTCEN. Al 1 other required test instrumentationshal 1 be furni shed by the contractor. Instrument recording systems,including recorders and telemetry equipment, shal 1 be compatible with theground station equipment at all test and demonstration locations. Allpeculiar test instrumentation procured to satisfy this demonstrationshal 1 be labeled by incorporating “SF” as the last two characters of thei tern’s model number. Al 1 contractor-furni shed special f 1 Ight testinstrumentation used for the demonstration shal 1 be made available to theNavy for the duration of fol low-on T&E programs.

3.1 .5.2 Instal 1ation. c alibratio n. and maintenance The contractorshall Install , calibrate, operate, maintain, and repair ”all aircraftinstrumentation used in performing the demonstrations. Al 1instrumentatlon shall be installed in accordance with normal aircraftprocedures and guldel lnes as approved by the Test Authority. Al 1

9


MI L-D-8708 C(AS)

transducers shall be properly located, properly damped, have flatfrequency response characteristics commensurate with the frequencies ofexcitation of the variable to be measured, and be properly mounted toassure valid measurements and freedom from extraneous excitations.Errors-resulting from time delays or phase shifts between measuredparameters shal 1 be commensurate with the accuracy requirements of thetest program and shal 1 be documented for contractor-i nstal ledinstrumentation. To the maximum extent possible, end-to-end cal ibrationsof all parameters shall be made through the aircraft instrumentationsystem to at 1 east the maximum range of excitation expected during thecourse of the demonstration. Cal ibration may be performed by transducersubstitution techniques for those transducers for which an accuratesubstitution model exists; however, this method is allowed only when anactual end-to-end cal {bration cannot be performed. Transferredlaboratory calibrations shal 1 be unacceptable, except in those cases inwhich the actual end-to-end calibration or transducer substitutionmethods are determined to be impossible or impractical. The proposedmethods for instrument calibration shall be approved by the TestAuthority. Cal i bration test data shal 1 be obtained and recorded duringboth increasing and decreasing values of the parameter which theinstrument is intended to measure. Files provided to the ground stationsfor calibration and format descriptions shall be compatible with theexisting installation. After completion of the instrumentationinstallation, an EMC/EMI Safety-Of-Flight Test (SOFT) shal 1 be conductedon the instrumentation prior to flight.

All strain gage installations shall be installed to minimize interactionsor “cross-talk” during combined loadings. Interactions which do existshal 1 be properly accounted for during the calibration. Calibrationprocedures shal 1 include compensation for temperature effects. Straingage installations that cannot be calibrated may be used only if i t canbe shown, prior to installation, that the computed loads from suchinstallation are meaningful and useful and that the methods of gageapplication, load calculations from gage output, gage factor, andphysical constraints of the member are acceptable to the Test Authority.

3.1 .5.3 Check-calibrations. Check-calibrations of al 1 contractor-installed instrumentation shall be performed or witnessed by the TestAuthority before the demonstration. Instrumentation system static anddynamic response checks shal 1 be made through the recordingsystem/telemetry transmitters and ground station equipment. Nhere suchcheck-calibrations show significant departures from previouscalibrations, a complete recalibration shal 1 be performed.

3.1 .5.4 Re-calibrations. Demonstration instrumentation shal 1 be re-calibrated whenever a transducer is changed or repai red, when the dataappears incorrect or questionable as determined by the Test Authority,when the check-calibration identifies a significant deviation, and at theconclusion of the demonstration. The results of al 1 re-cal ibration foreach of the demonstration aircraft shall be reported as revisions to thecalibration appendices of the Demonstration Instrumentation Report.

3.1 .5.5 Acceptance and witnessinci Procedures. The Test Authoritywill formally accept all instrumentation system installations for eachdemonstration aircraft at the location at which the demonstration testsare to be performed. Inspection of the instrumentation may be performed

10


MI L-D-8708C(AS)

at the contractor’s faci li ty or other designated location, beforedelivery of the aircraft at the test location. During or before theforegoing acceptance of instrumentation installations, the Test Authori tywi 1 L witness contractor calibrations of the complete instrumentationsystem:. All instrumentation installations and calibrations will bewitnessed by representatives of the Test Authority. Acceptance shal 1 bebased on the fol lowing:

a. Installation.

1.

2.

3.

4.

Acceptable workmanship and proper location and mounting ofal 1 instruments and related systems.

No deleterious effects on measurement accuracy and datareduction in the signal conditioning equipment.

The equipment has been evaluated to ensure that it wi 11operate satisfactorily in the expected environment.

Instrumentation recording systems, including magnetic taperecorders and telemetry equi Dment are compatible with groundstation equipmentlocations.

b. Calibrations.

1. Valid calibration

at al 1 designated test and demonstration

standards are used.

2. Cal ibrations are repeatable.

3. The instruments have no adverse hysteresis effects.

4. Each instrument is calibrated to at least the maximum valueof the parameter expected to be obtained during thedemonstration.

3.1.6 ~s. Contractor flight operationsshall be conducted in accordance with NAVAIRINST 3710.1. This includesinternal procedures, qualifications, and proficiency of pilots, crewmembers and ground personnel . Anthropometri c restrictions of NAVAIRINST3710.9 shal 1 apply to contractor pi lots.

3.1 .6.1 Prerequisites for first fliah~. Prior to first flight thecontractor shal 1 have:

a. Completed static test conditions requi red by the Aircraft WeaponSystems Engineering Design Examinations Addendum to at 1 east 150percent of the design limit load for the conditions to be flown.For cases where loads are not well predicted or well controlledin flight, static test to ultimate load shall be performed.

b. Performed the structural dynamic tests (such as, flutter modelwind tunnel tests, compliance tests and ground vibration modaltests).

c. Performed the flight control system ground survey.

11


d.

e.

f.

9.

h.

i.

j.

k.

1.

m.

MI L-D-8708 C(AS)

Performed the propulsion system ground survey.

Performed fire detection system tests in accordance withMI L-F-7872 or MI L-F-23447.

Demonstrated that safe egress from the aircraft WI 11 bepracticable in event of an in-flight emergency.

Performed a safety assessment and an EMC/EMI Safety-Of-FlightTest (SOFT).

Submitted the fol 10wI ng \ n accordance wt th the CDRL:

1.

2.

3.

4.

5.

6.

7.

8.

The initial aeroelastic stability analyses report, fluttermodel wind tunnel test report(s), compl lance test dataresults, and ground vibration modal test results.

Estimated flylng qualitles.

The results of the

The results of the

The results of the

Weight and balance

The

The

Received

1. The

2. The

3. The

results of the

Demonstration,

flight control system ground survey.

propulsion system ground survey.

fire detection system tests.

data as specified by MIL-H-25140.

safety assessment.

Planning and Progress Report.

approval of the fol lowing In accordance with the CDRL:

Demonstration Program Plan.

Demonstration Instrumentation Report.

Flight Operations and Fllght Plan.

Performed external Electromagnetic Environment (EME) analyses Inand around the fl ight test area.

Made suitable arrangements for flight monitoring.

Obtained Inspection and acceptance of the aircraft (form DD-250).

Obtained a f 1 ight clearance ! n accordance WI th NAVAIRINST13034.1.

3.1 .6.2 Release for f 1 iaht and o~erat ina limits. Flightauthorization shal 1 be requested in accordance with the f 1 ight clearanceprocedures defined in NAVAIRINST 13034.1. F1 ight release may be dentedif safety of flight Is not substantiated. Prior to release for flight,the contractor shall prepare flight plans covering tests anddemonstrations, procedures, and planned operating 1 Imits to be fol lowed

12


MI L-D-8708 C(AS)

by the flight test crew. After initial approval and release for flight,flight plans need not be resubmitted for additional flights i f operating1 imits or other criteria upon which the approval was based remain val id.Operating 1 imits shal 1 not exceed any of the following:

.,-,

a. Those authorized by the acquiring activity or its designatedrepresentative.

b. Those which the contractor has determined to be safe based on,but not limited to, the following:

1. Results of analyses of the whole aircraft and its componentparts from the aerodynamic, aeroelastic stabi 1 ity,structural, and functional viewpoints.

2. Status of completion of tests which may, by thisspecification or the documents 1 i steal herein, be required tobe completed as a prerequisite for certain f 1 ights.

3. Review of observations and data recorded during priorflights which have been reduced and extrapolated to themaximum extent practicable. The Test Authority may waivereduction and extrapolation of the recorded data whenreduction and extrapolation of the data are not necessaryfor safety prior to further flight testing. Any waivers toexpedite flight testing shal 1 not negate other provisions ofthis specification relating to submittal of data.

c. Those for which an ultimate factor of safety of 1.5 has beendemonstrated by tests and analyses accepted by the procuringactivity. In the event that such tests have not been performed,the operating limits permitted shal 1 not be more critical thanthose for which a factor of safety of 2.0 for metal 1 ic structureand 3.0 for composite material structure has been substantiatedby analyses approved by the acqui ring activity.

3.1 .6.3 Normal fliqht limits. Normally, the initial flightauthorization by the acquiring activity will be to the limits of “normalflying” which, for demonstration purposes, shal 1 mean that:

a. Normal takeoffs and landings are authorized.

b. Flying in a normal attitude is authorized with the followinglimitations:

1. A normal load factor of 2 shal 1 not be exceeded.

2. An angle of bank of 60 degrees shal 1 not be exceeded.

3. Flight controls, engine controls, and other systems,innovations, or appurtenances shal 1 not be moved or operatedso as to result in rapid or abrupt aircraft responses.

13


MI L-D-8708C(AS)

4. The speed at any altitude shall not exceed either 1.1 timesthe maximum speed attainable in sustained level flight atthat altitude with maximum continuous power or thrust, or0.75 times the minimum critical flutter speed at that

.,. -. altitude, or 0.75 times the design limit speed (V ) at thataltitude, whichever is less. \The minimum critics flutterspeed for this purpose shal 1 be that determined by analysesor data accepted by the acquiring activity.

3.1.6.4 Fliqht eouinmert. Standard Navy flight gear and relatedequipment shal 1 be uti 1 ized for the tests and demonstrations requiredherein, wherever possible. I/here contractor developed f 1 ight equipmentis required, it shal 1 be provided and used by the contractor and be madeavailable for use by Navy personnel during DT-11 evaluations.

3.2.1 Tests and demonstration The structural demonstration programshall consist of structural buildup tests and a formal structural flightand ground demonstration. These tests shall also include structural dynamic .flight tests to ensure that the aircraft, with and without stores, is freefrom flutter, divergence, and other aeroelastic instabilities, structurallydamaging vi brations/aeroacousti cs, and excessive vibration at crew andpassenger stations throughout the flight envelope.

3.2.2 ~. The aircraft to be used for thedemonstration tests shall be ldentlcal to the production aircraft in allstructural and aerodynamic aspects and shal 1 be designated by theacquiring activity. After release of the aircraft for testing, noreplacements, alterations, changes or adjustments other than thoserequired by normal maintenance shal 1 be made. When substantial changesthat affect either the structure, aerodynamics, or the structuralintegrity are made by the contractor, the Structural Demonstration TestPlan shall be modified for the demonstration aircraft or provisions madein the plan to test a subsequent Instrumented and calibrated aircraft.Any change shal 1 require approval from the acquiring activity.

3.2.2.1 G~M. The test conditions specified for thestructural flight demonstration shall be attained at the 8asic FlightDesign Gross Weight (BFDGW), Maximum Flight Design Gross Weight (MFDGW),or other critical gross weights from Minimum Flight Height to MFDGW.Proposed alternate gross weight shal 1 be submitted to the acquiringactivity via the Test Authority. Alternate gross weights may be proposedprovided that:

a. The load factors and magnitude and distribution of weight aresuch that all parts of the aircraft will be loaded at least ascritically as if the tests were made at the specified grossweights and center-of-gravity positions.

b. The products of load factor times gross weight are not lower thanthose specified herein.

14


MI L-D-8708C(AS)

3.2.3 Fliaht test instrumentation. Instrumentation shal 1 be asdefined in the Demonstration Instrumentation Report. Instrumentationshal 1 be adequate to measure the parameters required for the structuraldemonstration tests specified herein. The location of theinstrumentation shal 1 permit correlation between the flight andlaboratory tests. Local strain instrumentation shal 1 be provided topermit correlation between flight test, static test, and fatigue testarticles. Al 1 structural instrumentation shal 1 measure loads andresponses i n the identical coordinate reference system as the contractorload analyses.

3.2.3.1 Strut tural fl iaht loads instrumentation. Instrumentationshal 1 be provided to measure a minimum of 3 wing spanwise stations on theleft wing (root, fold, mid) and at least the wing root on the right wingfor determining distribution of bending moment, chordwi se moment,vertical shear, chordwi se shear, and torsion. Instrumentation shal 1 beprovided to measure forward and aft fuselage vertical and lateral shearloads and bending moments. Instrumentation shal 1 be provided to measurehorizontal and vertical stabilizer bending, shear, and torsion loads.Instrumentation shal 1 be provided for load and/or hinge momentmeasurements including, but not limited to: landing gear doors, weaponbay doors, auxiliary lift and drag devices including speed brakes, flapsand slats, control surfaces and devices including vectored thrust,external and internal store/carriage including store to pylon and pylonto wing or aircraft structure interfaces, retraction and extensiondevices, engine mounts, refueling probe, engine duct pressures and fuelpressures. Instrumentation shal 1 be provided for temperaturemeasurements of those areas of the airframe subjected to temperatureswhich might adversely affect their structural characteristics.Accelerometers shal 1 be located to permit determination of inertial loaddistributions for correlation with static and dynamic loads. Localstrain instrumentation shall be provided at critical structural locationswhere load instrumentation is not applicable. Al 1 instrumentationrequi red for the structural fatigue monitoring system shall be providedon the test aircraft. Instrumentation shall include pilot control inputand force, control surface response. aircraft attitudes, accelerations,and velocities, both angular and translational about all aircraft axes.

3.2.3.2 ~.Instrumentation shall be provided to measure the following:

a. Landing gear loads in three axes and the corresponding shockstrut stroke.

b. Arresting hook and damper, launch bar, and holdback fitting axialloads, side loads, bending moments, torque, and angular positionsin two axes.

c. Internal and external store interface and pylon/wing or aircraftstructure interface loads and internal extension and retractiondevice(s) laads. In addition, measurement of the translationaland rotational accelerations of the store are required.

d. Engine loads.

15


e. Pi lot control inputs

MI L-D-8708C(AS)

and control surface positions.

f. Loads reaui red in oaraaraoh 3.2.3.1 if structural desian isgoverned “by ground’ load chndi tions.

. .

., .-.g. Wing folding, locking and stowage mechanism loads.

h. Aircraft center-of-gravity load factors, Nx, Ny, Nz, ai rcraftweight, rol 1 rate, sink speed, and engaging speed into arrestinggear.

i. Landing gear rotational speeds.

j. Landing gear axle accelerations in three axes.

k. Acceleration in three axes for aircraft center-of-gravity,pi lot’s seats and other locations as required for compari son oftest data with analytical predictions.

1. Strains at critical locations.

3.2.3.3 Structural instrumentation calibration. Calibrationprocedures used for the structural load instrumentation shal 1 utilizetechniques establ i shed by NACA reports and NASA for zone load methods.All structural load instrumentation shal 1 be calibrated to 100 percent ofdesign limit load. Calibration procedures for the structural loadinstrumentation shall be defined In the Demonstration InstrumentationReport.

3.2.4 co ntractor demonstration reau i rements. The structuraldemonstration program shall consist of:

a. 80 percent and 100 percent buildup tests to characterize theaircraft loads, kinematics, and surface position relationshipsand to verify the basic al rcraft design load analyses for bothcritical design conditions and load trends. This testing shallinclude:

1. Load survey of aircraft structures tests.

2. Structural flight limitation tests.

3. Store release structural load survey tests.

4. Taxi, takeoff and landing tests.

b. A formal structural flight and graund loads demonstration of al 1the critical loading conditions throughout the design flightenvelope and design carrier sui tabi 1 i ty/landing envelope requi redby the detai 1 specification.

16


MI L-D-8708C(AS)

3.2.4.1 Fli~m. The 80 percent and 100 percentild-uload survey and flight limitation tests shall be conducted prior to theformal structural fllght demonstration tests and shall include the testsspecified in paragraph 3.2.4.1.1, 3.2.4.1.2, and 3.2.4.1.3. Criticalcombinations of gross weight, center-of-gravity position, altitude,speed, load factor, Mach number, cockpit control displacement, andcontrol surface authority shal 1 be tested. Maneuver methodology shal 1 bein accordance with the design maneuvers of MI L-A-8861 , however, whereload trends indicate critical conditions within the flight and maneuverenvelopes, additional surveys shall be performed to ensure identificationof critical load conditions and structural deflclencles.

3.2.4.1.1 .Fliaht tests for load sur ev o f airframe structure The80 percent and 100 percent fllght loads [urvey shall include all ~ritlcalvariations of gross weight, center-of-gravity, store configuration,aerodynamic configuration including flaps, slats and speed 1 imitlngdevices, pi lot control inputs, both abrupt and steady, and thrustvectorl ng and shal 1 be investigated i n accordance with Tabl”e IA asspecified herein. The tests shall include the clean aircraftconfiguration and the most critical store conf iguratlon for Table IA.Other store and/or aircraft configurations shal 1 be surveyed asdetermined from load trends establ i shed from the clean and critical storesurvey requi red by Table IA. Other store configurations may be requiredto determine the crl tical store configuration. Al 1 configurations to betested shall be approved by the acquiring activity. Prior to 100 percenttesting, the results of the 80 percent tests shall be submitted to theacquiring activity for approval .

3.2.4.1.2 Structural f liaht limits tions tests Structural flightlimitations tests shall be conducted for the clean ”aircraftconfiguration, and the three most critical store configuration(s) (ifapplicable). The tests shal 1 be conducted in accordance with Table IB asfol lows:

a. The tests of Table IB shall be performed at:

1. The basic flight design gross weight whtch includes thestores specified In the detail specification for thecritical stores configuration.

2. The maximum aft center-of-gravity position with the landinggear retracted, including the growth factor specified i n thedetail specification.

3. The maximum forward center-of-gravity position with thelanding gear retracted, including the growth factorspecified in the detail specification.

b. The variation of maximum dynaml c normal force coefficient withMach number tests shall be performed in accordance with Table IBas specified herein. The contractor shal 1 select and submit tothe acquiring activity for approval , critical combinations ofloading, configuration, gross weight, and center-of-gravityposition for the demonstration of Test “a” of Table IB. Thetests shal 1 be performed at an altitude not greater than 20,000feet, with engine(s) operating at that thrust which wi 11 result

17


r

TABLE 1A. F1ioht tests fOr I oad SUFJeV St ructur~.

1 I 2 I 3 I 4Sst St ructure Critical loading Maneuvers

( \ t

a mRoot Bending and torsion

(positive and negative)

Outer panel B#:: (positive & negative)

Fold joint Bending(if applicable) Torsion

Symmetric (steady habrupt)

Pull-upsPush-overs

Asymmetric (abrupt)R#]yg pull-outs

Oi rectional (steady) andabrupt) maneuvers

Translational (abrupt)maneuvers(if applicable)

ILeading edge ITorsionextension Wing attachments(if applicable) I

b IFuselaqR IRend{ng (positive & negative)FotwardCenter

IAft IBend{ng (positive 6 negative)Torsion

1

c Emc.ennaggHorizontal Bending (positive 6 negative)

Hinge momentPanel loads

Vertical Bending (positive & negative)Panel loadsTorsion

d CC.ntrol rfaRudder,Elevator Hinge momentsLateralControls - Hinge mcmentsFlaps LE 6 TE Hinge mcments

e IExternal store ICritical for fuselage wingstations and w{”g store station I,

f Other com~ne:t; {:: may bah~ique to thee5 ions a a D ed bv t s suet ificatio”,

5Remarks

The load survey data shall be obtainedfor all of the maneuvers specified incolumn 4 at a minimum of 6 altitudesand a minimum of 10 tlach nwbersat each altitude. The altitudes and

,:

xirspeeds selectad shall be sufficientto en$ure the attainment of the critical ‘loading to an accuracy of 5% throughoutthe full speed, load factor envelopespecified in the detail specifications whichencompasses the maximum loadings of column 3for the airframe components specified incolumn 2. Additional increments shall be {ncludedto ensure that no new critical conditions existfor the airframe. The method for performingthe maneuvers defined ifi colunm 4 shall be inaccordance with the design maneuvers of HIL-A-B861.


—

~

‘est—

a

2

Name

PHAA6 recovery

-

Factor

At least

ma

apeed to be attained in camoinacioaith requi red load factor

=/3%5‘here:

: Speed for the test, knots,x = Design 1 imi t load. factorI : Weight of the a+ rpla?e

specified for the test, pounds, : Surf Ice area, sq. ft.),0 : Air density. slugs/cu. ft.

+am&a z ttaximum dyn~ic normalforce coefficient ●sdetermined for the CW.s N data

( = 1.2S for H=O.6( : 1.0 for H=l. OK a (1.625 - .625 M) for 0.6 to 1.0

(The above values for K are thespecified design values. ) NOTC:

::%?$ :U%ger::a%rthis test...

~

altitude

No greaterthan 7500 ft.

Specizl requirements

for airplanes ha.ing bmb-bay doors,, thesi’ testshal 1 be performed wi th the bom~bay doors ,oPen.These tests shall be perfomed so as to develop:[1) The specified load factor it speed not

greater than the specified speed or al terna-tively,

(2) The specified load factor at the minimumspeed at Mnich the load factor can be de.e-lmed in a svmetrical pull-out in a verticalpl~na by ippiy{ng maxiiwm longitudinal-controlforce [see definitions) in not mm tbn 0.s!econd and maintaining that force unti 1 themaximum attainable load factor has been reached.

If the results of dcvelopmtntal flights indicatethat attainment of the specified conditions by [ 1).above, is not possible znd that compliance withthe procedure of (2), above, would result in exceed-ing the limi t stren th of the ai rplane, the coc-

itrzctor, by means o tnalyses, wind-tunnel tests,andlor flight tests. shall datermin. thm designchanges needed to permit attaimtent of the speci-fied conditions with the procedure of (2), abave.shall install the changes, and shall demonstrate theip.ci fied conditions. RcG.avery shill b, -da byapply~ng maxi- longitudinal-control force in theOPPL’SI te direction until maximum up-stabilizer loadhas been ●ttained Con$istcnt with nfe re$overyprocedures.


—

—

c

d

2Name

Landingequipmentoperation

Landingconf i gu-rationpull-out

Scrambletake-off

_&_-

factor

)ptional

at least2.0

)ptional

TABLE IB. si~ct. ral fliaht limitations te$t s - Continued.

4Speed to be attained in combinationwith required load factor

Maximum attainable as limited byeffectiveness of operating Systm,safe flying qualities, or limitstrength of structure or system,whichever is most critical

Not lower than the maximum W forVLF as specified in HIL-.W26O.

As specified in column 6.

-

al ti tude

Optional

Optional

As specifiedin column 6.

6Special requirements

,.

Perform tests far each of the following {terns:( 1 ) Extend landing gear.(2) Flight with landing gear fully extended.(3) Extend high lift devices.(4) Flight with high lift devices fully extended.(5) Operation of the sliding portions of cockpit

enclosures unless operation of sliding por-tions in flight is limited by design require-ments to only mergoncies (separately andcollectively if such operation is possibl e.)

(6) OPeration of any other devices that are usedfor landing or in the landing approach.

Oevel.ap specified load factor and speed in thelanding approach configuration.

Perfotm take+ff with airplane in field take-offconfiguration, maintaining cc+nbat power from startof run until test is completed without use ofspeed-reduction devices. Actuate, in proper sequenceall cockpit controls for retracting, closing orreposi tioning landing gears, high-1 ift devices,pilot enclosures, and any other app”rte”an~e~ thatretract, close, or go into different positionsduring transition. frca! take-off to the climb con-figuration, and record history of relative positionsof each appurtenance with equivalent ai rspeed unti 1each reaches final position for climb. The, altitudeshall not exceed 200 feet above the runway surfaceuntil the best-cl i!d airspeed is reached, Repeat thetest: for carrier-type (Continued on next page)


TABLE IB. firuct ural fliqht limitations testi - Continued.

1 2 3 4Test Name

65Load Speed to be attained in combination Pressure

factorSpecial requirements

with requi red load factor altitude

,,

(Continued from previous page) ,,

airplanes in catapult take-off configurationif different from field take-off configuration.

e One As speci - As specified in column bengine out fied in

(1) Not greater For multi-engine airplanes, only, with one enginethan 7500 ft. not operating. At each requi red altitude attain

CO1umn 6 and also (2) (1) greater of all-engines-operating VHRT or vwi thin 2000 ft. W(as applicable) or maximum-safe speed at test a ltudeat which VHRT with no specified pull-out load factor and (2)Or VMT (a$ s~etrical Pull-out to greater of 2.25 or maxi mum-applicable) safe load factor at speed not less than all engineswi th full -ccm- operating v~T or VWT (as applicable) at testbat-thrust at altitudes.combat weightis attained.


MI L-D-8708 C(AS)

in the maximum dynamic normal force coefficient, but notexceeding maximum continuous, and under the fol lowing conditions:

1

2

3

The aircraft shal 1 be at a speed not less than 20 knotsabove the stalling speed and shall be trimmed for zerocontrol forces for unity load factor. The speed shall bedecreased at a rate not to exceed one knot per second,holding the wings laterally level until a fully developedstall is attained. A fully developed stal 1 is attained whenthe aircraft has developed ful 1 post stal 1 motions and thecontrol stick has been moved and held to the ful 1 aftposition.

The aircraft shal 1 be at a speed greater than the speedrequi red for Test “a” of Table IB and shal 1 be trimmed forzero control forces for level flight. The aircraft shal 1enter a windup turn and perform an accelerated stall at aload factor of at least 0.95 nzmax.

The aircraft shal 1 Derform at 1 east two additionalaccelerated stal 1s as described in subparagraph 1. above,except that the speeds shal 1 be incremental Mach numbersbetween the stalling speeds of subparagraphs 1. and 2.above, with corresponding incremental load factors.

3.2.4 .1.3 Store release structural load survey. A store releasestructural load survey shall be performed for all critical store releaseconditions. This shal 1 include both airframe critical loads and adjacentstore critical loads. The survey shall be performed using a buildupapproach to the maximum release load factor. The aircraft gross weightshall be the critical design gross weight as defined in the detailspecification. Testing shal 1 be performed at the critical center-of-gravity and aircraft configuration. Stores shall be released duringsymmetrical pul l-up conditions.

3.2.4 .1.4 Enaine oDeration durina tests. Tests shall be performedwith maximum continuous power (or thrust) and RPM of the power plant(s),except for multi-engine aircraft where Test “e” of Table IB shal 1 beperformed with one engine inoperative. The engine selected to beinoperative for Test “e” shal 1 be approved by the Test Authority. Engineoperation for V/STOL ai rcraft shal 1 be the maximum vectored thrustrequi red to attain maximum performance. Ouring transitional operation,the vectored thrust shal 1 be distributed to obtain maximum translationalvelocity in minimum transition time. Maximum differential thrust shallbe used for V/STOL tests requiring asymmetric thrust.

3.2.4 .1.5 ODeration of fliqht co ntrol s Vs terns. The influence ofeach control system (as appl i cable) on control surface movements(authority) and aircraft flight characteristics shall be determinedduring the structural flight tests. These systems are:

a. Systems operating independently of pilot control which can movethe control surfaces independently either by design for theirintended use or because of malfunction, e.g. aerodynamic slats,autopi lot. The Test Authority shall determine, for each of the

22


MI L-D-8708 C(AS)

demonstration tests specified, whether the system is to beengaged or disengaged during the test.

b. Sys terns dependent on pi lot control

1. Direct systems ( includtng boosted systems) in which maximumdisplacements attainable may be 1 imlted by normal stops ~nthe control system or limited by the alrloads which exceedthe maximum control system output. Subject to approval bythe Test Authortty, these maximum control displacements maybe substituted for the control forces specified for thedemonstration tests of Table IC.

2. Stahl 1 i ty augmented systems where the pi lot input does notd~rectly establ~sh the control surface(s) position(s), i.e. ,control surface authority of fly-by-wire, hand-oriented,computer, and active controls.

3. Translational control systems where the pl lot input providestranslational changes to altitude and sidewl se directions,i.e. , vectored-thrust, direct-1 ift control, and direct-side-force control through means other than the conventionalcontrol surface displacements.

3.2.4 .1.5.1 m. Al 1 tests shal 1 be performed W1 th the aircrafttrimmed for a control force within 10 pounds of zero for each control Insteady wings lateral ly level fl lght at the speed specified for the test.The tolerance “within 10 pounds of” 1s authorized to el Iminateunnecessarily precise trimming during structural demonstration tests.However, such a tolerance does not justify any deviation from flyingqualities design requirements. For aircraft having stabilityaugmentation control systems, no lateral trim tolerance wi 11 be permittedfor symmetrical maneuvers.

3.2.4 .1.5.2 Max i mum cent rol authority Subject to approval of theTest Authority, the maximum control authority attainable, as I imi ted bynormal stops or avionic 1 imits in the control systems, may be substitutedfor the control forces specified for the tests and demonstrations.

3.2.4.1.6 Qoeratlo n of aormrtenances. Ouring buildup flights,appurtenances which can be put into continuous motion (such as rotationof radar antenna) , which can be extended or rotated to differentpositions (such as an extensible radar antenna or rotating bomb-baydoor), or which can be suddenly extended and suddenly retracted (such asan extensible rocket launcher), shall be operated sufficiently todetermine, by a combination of test data and calculations, the effects onaircraft loads and motions up to the V-n 1 imi ts required for structuraldesign of the particular item. This determination shall be discussedfully in the Demonstration Planning and Progress Report. The acquiringactivity will select the positions and/or motions of appurtenancesrequired for structural flight limitation tests if such positions andmotions are not specified in Table 16. During and immediately after eachflight performed during structural limitation tests, the satisfactoryoperation of appurtenances subjected to high loads shal 1 be demonstrated.

23


1 2 I 3Test I Name I Speed

-

c IHigh al ti tudePL4A

e ILow speedrollingpull-out I

-1----f High speed

roll ingpull-out

9 Rolls

Gh Pushover

Sideslips

Fj Rudderreversal

k Scramble

1 I One-engineout

MI L-u-tt/UML(A>)

TABLE IC. ,Structural demonstration tests.

4Al ti tude

Critical

Sea 1evel

Critical

+

factor

‘ma x

.8 nrnax

:ri tical

%ax

lotional

-&---

Critical

7Remarks

Steady and abrupt

Load factor for fighterand attack type - nmax.Load factor in column 5 is atmaneuver initiation.

Load factor for fighter andattack type y nm x.

?Load factor

in column 5 Is a maneuverinitiation.

Both lg and -lg for Fighterand/or Attack Aircraft.

Bo~h, steady and abrupt atcrl tlcal low and high ai rspwad.

As specified for test d inTable IB.

24


J_Test

.

—

n

—

0

—

P

—

NOTE :

2Name

.,.:.Transi ti.a”aTnaneuvers (asappl i cable)

Flight cont-rol systemnal functi ons

Get home

Low speedPU11 up androl 1

3Speed

Critical

MI L-D-8708C(AS)

TABLE lC. St ructural demonstrate on tests - Continued.

Cri tical

*

factor

Critical

t+ or N,

Critical

6CG

Critical

JRemarks

Haximum pilot control inputto provide specified displace-ment in the vertical or sidewisedirections to achieve the spec-

~L+ and/or N,

For air lanes equipped with SASEor fly y wire computer cont-

rolled flight control systems,the maximum safe limits shallbe demonstrated W{ th one controlsystems inoperative. Th@ sele-ction of the failed systemshall be made by the TestAutho ritv.

For airplanes equipped with SASor fly by wire computer cont-rolled flight control system anda manual back-up system the maxi-mum safe 1 imi ts shall be demon-strated with only the manualSvste m ooe rative.

Takeoff and landing

1. The aircraft canf igurations to be used for these tests shall be the clean configuration and the criticalstores configuration(s) (if applicable) .

I 25

I — . ——. —


MI L-D-8708 C(AS)

3.2.4.2 Formal structural fl iaht and around demonstrations. Formalflight and ground demonstrations shal 1 be conducted fol lowing theanalysis and approval of the structural flight and ground bui ldup dataand following the Structural F1 ight Oemonstration Planning and theStructural Ground Loads and Carrier Sui tabi 1 ity Demonstration PlanningConferences. Prior to release of the aircraft for the formal structuraldemonstrations of Tables IC, 11A or IIB, the data resulting from the 80percent and 100 percent flight and ground buildup tests shall be includedin the Oemonstration Planning and Progress Reports and the OemonstrationReport. Specific conditions and parameters to be demonstrated shal 1 berecommended. Aircraft designated for the demonstration shal 1 be given anin-depth structural inspection prior to the demonstration. Additionalperiodic structural inspections shal 1 be performed fol lowing tests wherecritical load factors are experienced. A final in-depth inspection shallbe performed fol lowing completion of the demonstrations.

3.2.4 .2.1 Structural fl iaht demonstration. The maneuvers specifiedin Table IC or as modified at the Structural F1 ight OemonstrationPlanning Conference shal 1 be performed. A single aircraft shall be usedfor the dives and pull-ups. Pi lot control input/maneuver method shal 1 bein accordance with MI L-A-8861 or as determined during the structuralbuildup tests, whichever results in the maximum/critical loads.

3.2.4 .2.1.1 Structural dvnamic fliaht demonstration. The structuraldynamic flight test program shal 1 be performed in accordance withMIL-A-8B70.

3.2.4 .2.1.1.1 Aeroelastic stability fliaht tests. Aeroelasticstabi 1 i ty flight tests shal 1 be performed in accordance with therequirements of MI L-A-8870, concurrent with flight envelope expansion upto design limit speeds. Aeroelastic stability flight tests shall beperformed for the clean configuration and ten additional configurationsselected from the primary mission configuration, alternate mission(s)configuration(s), and other store(s) configuration(s). Theconfigurations shal 1 be approved by the procuring activity, Prior toauthorization to proceed with aeroelastic stability flight testing andflight speed envelope expansion, the prerequi site supporting test resultsand documentation requi red by the applicable Aircraft Weapon SystemsEngineering Design Examinations Addendum shal 1 have been submitted inaccordance with the CORL including:

a. Intermediate Aeroelastic Analysis Report.

b. Flutter Model Nind Tunnel Test Report(s).

c. Flutter Compliance Data Report,

d. Ground Vibration Modal Test Report(s).

e. Thermoplastic Test Report.

f. Rigidity Test Report.

26


TABLE 11A. Field landinq test$.

1 2 3 4 5 6

ly~e, g: Sink~~~ speedTest

Hgr~zo~~gl Pitch attitude Roll angle I:) qrees es

a Carrier based 10 1 .05VpAmi n Tal 1 down -3 Optional

Mean ~1.5

c Ih ree point +3

d 5 Uptlonal Not less than 5

e Lan -Dasedtra!ner

17 iali Oown -3 Uptlonai

Mean ~ 1.5

9 lh ree Point +3

85 Uptlonal Not less than 5

1 L dbid ‘oe!!e~ta ~nd-

lai I uown -3 uptlonal

J based trainer Mean ~l. b

Ih ree point +3

5 uptlonal

m Not less than 5

NOTES :

1.

2.

3.

The pitch attitudes for tai 1 down and three point are defined in MIL-A-8863; the mean attitude isas defined in MI L-A-8863.

Tolerances for pitch and rol l-attitudes are fl degree.

Tolerances for horizontal speeds are *1O knots.


MI L-D-8708 c(As)

TABLE llB. ~.

2 3 4 5 6Sinking Her{ zontal Pitch Rollspeed speed altitude al ti tude Remarks. .

. OBB5 vb

VA + 15 KTS Not greater optional Perform once to the+6.1 FS than mea” conditions speclf-

- 4.5 deg ied or alternatlvel:3 times but withsinking speed notless than 0.8 timesthe specified.

Not less than Perform once to themean + 4.5 condi ti0n5 SpOC{ f-degrees fed or altcmatlvtl!

3 tlmss but withslnkln spmd mk

IIlet$ t m o.B t{megtho %pec{ fled.

Hea” plus Par IOi-0 once 10 tlMor minus3 degrees IcondltlDn! spot r-

Ied or allarnal. v41]3 times but with

t$Inkln spa-d OOtless t an 0.8 timesthe sp?cif{ed.

.0885 VA Optional 7 degrees+ 3 FPS

.0885 VA Optional Yaw angle not lessthan 6 degrees.

NOTE: Symbols of this table are defined in HIL-A-BB63.

28


MI L-D-8708 C(AS)

3.2.4 .2.1.1.2 Vibration fliaht tests. Vibration flight tests shallbe performed i n accordance with MI L-A-8870. These tests shal 1 includeinstrumented external fuel tanks and mi ssi les to determine the vibrationresponse envi ronments.

‘3.2.4 .2.1.1.3 Aeroacoustic around and fliaht tests. Aeroacousticground and flight tests shal 1 be performed in accordance with MI L-A-8870.The aeroacoustic ground tests shal 1 be completed prior to accrual of 50flight hours on any flight test aircraft.

3.2.4 .2.1.1.4 ~ lif ffects on ntrol urfac tabs. anwinafolds. Freeplay measurements and rigidity tests shal 1 be performedon al 1 control surfaces, tabs and wingfolds on three flight test aircraftin accordance with MI L-A-8870. Records shal 1 be maintained on theseaircraft to track any deterioration in freeplay and rotational stiffnessor replacement of any component or associated parts during the flighttest and demonstration program.

3.2.4.2.2 Taxi. takeoff and landi na tests Weight distribution,including bal last to attain the specified gros~ weight and center-of-gravity positions shal 1 be approved by the acqui ring activity. Runwayroughness and unprepared field conditions shal 1 be as specified in thedetai 1 specification.

3.2.4 .2.2.1 Fi ld X~ fi ld andi ts.Taxi ing, (including turning, braking, and pivoting) and takeoff testsshal 1 be performed at selected gross weights and critical loadingconfigurations up to the maximum design gross weight. The field landingtests of Table 11A shall be performed at the landplane landing designgross weight and at selected critical loading configurations. The totalnumber of configurations to be tested shal 1 not be less than three. Atleast one configuration shal 1 be tested with the aircraft rol 1 ing overand impacting the cable of a field emergency arresting gear.

3.2.4 .2.2.2 Field Carrier LandinQ Practice ( FCLP) tests. Thelanding tests of Table 118 shall be performed at the weight for whichstrength is requi red for FCLP landings. The total number ofconfigurations to be tested for each test shal 1 not be 1 ess than three.The landings tests of Table IIB shall be performed on dry and repeated onwet concrete surfaces.

3.2.4 .2.2.3 Field emerc!ency a est a aea Compatibi 1 ity withstandard configured field emergenc~rarr~! ting ~~ar shal 1 be demonstrated.The ability af the arresting hook to engage and retain the arresting gearcross deck pendant shal 1 be demonstrated bath without braking and withmaximum braking with the anti-skid engaged, i f applicable. The testsshall be oerformed at the ~andolane landinq desiqn gross weiqht sDecifiedi n MI L-A-E860 atconfigurations.not be less thanknots.

3.2.4 .2.2.4requirements forparagraph 3.6.

selected critical gross w~ights-an~ loading-The total number of configurations to be tested shal 1two . The engaging speeds shall be up to 1.05 VpAmin + 25

Carrier suitability demonstration tests. The structuralcatapult launches and arrested landings are specified i n

29


MI L-D-8708 C(AS)

3.3 Aerodynamic demonstration tests.

I

3.3.1 Flight test Droaram. An aerodynamic flight test program shal 1be conducted to demonstrate flying qualities and performance, natural andartificial stal 1 warning, loss-of-control characteristics, and recoverytechniques.

3.3,2 Aircraft confimsration.

3.3,2.1 Fliaht te st vehicle. Except as discussed in “Emergencyrecovery devices ,“ “Inverted fuel /oil systems ,“ “Instrumentation, ” and“On-board cameras, ” the flight test vehicle shall be representative ofthe production aircraft in all significant respects.

3.3.2.2 Classification. Aircraft shall be placed in a class asspecified in MI L-F-8785. When operational missions and designcapabi 1 i ties indicate, an aircraft of one class shall be required to meetselected demonstration requirements ordinarily specified for aircraft ofanother class. The most stringent demonstration requirements shal 1 applywhenever an aircraft fai 1s to come clearly within one of two possibleclasses.

3.3.2.3 Gross weiqht and c.a. Dositions. The maximum aft andmaximum forward e.g. positions shall be the positions that can beobtained with any service loading combination attainable as specified inMI L-14-25140. The gross weight for a e.g. position shall approximate theservice loading that would occur with the e.g. position. Nhere neitherthe weight nor the e.g. is specified, the expected e.g. positions forservice use of the aircraft shall be used.

3.3.2.4 Emeraencv recoverv device. Unti 1 approach to stal 1 andspinning character sties of the aircraft have been determined, no spinsshal 1 be made without an approved emergency recovery device instal led andready for use. The emergency recovery device shall be installed withinthe normal contour of the aircraft, if at al 1 practicable, and shal 1 inno case be instal led in a manner so as to increase the effective fin areaof the aircraft and shal 1 not significantly change aircraft aerodynamics,inertia, or e.g. position. The contractor shall advise the acquiringactivity promptly if a determination is made that the installation of theemergency recovery device wi thin the normal contour of the aircraft isnot practicable. If the emergency recovery device is not tnstal ledwithin the normal contour of the aircraft, spins performed with thedevice instal led shal 1 be repeated with an aerodynamic productionconfigured aircraft. However, a requirement to validate departure orspin in a production configured aircraft wi 11 be contingent upon testresults that indicate spin demonstrations can be safely conducted withoutthe emergency recovery device instal led. Approval of the emergencyrecovery device installation shal 1 be obtained from the Test Authorityand, prior to commencement of high AOA and spin tests, successfuloperation of the device shal 1 be demonstrated, under control 1 edconditions, to at least an airspeed equivalent to the predicted maximumairspeed in a steady state spin.

30


MIL-D-8708C(AS)

3.3.2.5 Inverted fuel/oil SW terns. The flight test vehicle shallhave inverted fuel /oi 1 systems capable of sustaining engine operation forat least 60 seconds at Intermediate Rated Thrust and, if applicable, 15seconds at Maximum Afterburner Thrust. This applies to both single anddual, engine aircraft configurations.

3.3.3 Flioht test instrumentation. The contractor shal 1 provideonboard instrumentation in accordance with the DemonstrationInstrumentation Report. When very high angular rates are anticipated,variable range or additional rate gyros may be required to provideadequate resolution for the prestal 1 and post stal 1 conditions. Thefrequency response of the Instrumentation shal 1 be adequate to measurehigh frequency phenomena such as prestal 1 buffet. Except when actuatedduring emergency situations, flight test auxi 1 iary hydraulic andelectrical systems shall not restrict the mission time of the testaircraft. An emergency electrical power source shal 1 be provided toensure that loss of telemetry during high AOA testing will not occur.Actuation of the auxi 1 iary electrical power system shal 1 not interruptdata acquisition. The telemetry system shal 1 be capable of transmittingdata on a minimum acceptable set of critical parameters and provide audiocommunication capabi 1 ity between the airplane and ground station.Additional instrumentation shal 1 be provided for structural purposes whenpredictive studies or initial flight test results indicate that theairframe or store suspension equipment may experience stall/post stallloads near or above design values. To ensure compliance with the flightdemonstration test requirements as specified in paragraph 3.3.4.2, anerror analysis shal 1 be provided to verify the adequacy of the proposedinstrumentation.

3.3.3.1 ~. Cockpit displays in thetest vehicle, particularly instruments indicating airspeed, altitude,AOA, turn/slip, normal acceleration, stal 1 warning, attitude reference,and engine parameters shal 1 be those types to be instal led on theproduction aircraft. When special AOA, sideslip, and yaw rate indicatorsare provided, they shal 1 be easi ly readable and compatible in operationwith production indicators (e.g. , dials turning in the same direction).Either a specially designed negative pilot restraint system shall beprovided or the production pilot restraint system shall have beensuccessful ly tested on the NAVAIRDEVCEN centrifuge prior to conduct ofhigh AOA buildup or demonstration testing. A production pilot restraintsystem which has not been tested on the centrifuge shall be used onlyafter sufficient flight test results are available to indicate that crewstation angular rates and accelerations wi 11 not incapacitate or greatlyhinder the pi lot during application of recovery controls.

3.3.3.2 ~. Forward looking cameras, both cockpit andexternal, shal 1 be employed to document aircraft motions. These camerasshal 1 operate at 24 frames per second to al low true-time fi lm reviews.An adequate film supply shal 1 be provided to insure representativedocumentation during each test mission. Onboard cameras, that serve asan integral part of the quantitative data acquisition system may operateat any appropriate frame rate. A cockpit video camera shall be installedwith provisions for time tagging the video tape with the data acquisitionsystem. Unless otherwise suitably instrumented, the emergency recoverysystem shal 1 be covered by an onboard camera operating at an appropriate

31


MI L-D-8708 C(AS)

frame rate. External ly mounted cameras shal 1 be located to minimizeeffects on airplane aerodynamics.

3.3.4 Contractor demonstration reaui rements.

3.3.4.1 Fliaht test build-uD Droaram. A purposeful , milestoneapproach to high AOA flight test shal 1 be conducted to demonstratecompliance with the detai 1 specification requirements and obtain suitableinformation for the F1 ight Manual . Resistance to departure fromcontrol led flight and prevention of departures shal 1 be given the sameattention as that directed toward recovery from Post-Stal 1 Gyration (PSG)and spins. A concurrent objective of this demonstration is the reportingof detai 1 ed information for inclusion in the Emergency and FlightCharacter sties sections of the aircraft F1 ight Manual . A flight testbui id-up program consi sting of a flight simulation program and a flightverifi cation program shal 1 precede the formal demonstration of high AOAand spin character sti cs and Flying Qualities and Performance (FQ&P).The objective is to achieve an accurate definition of the aircraftaerodynamics, flight control system, store loadings, gross weight,center-of-gravity, and inertias as a function of AOA, sideslip, Machnumber, attitude, body axis rates: and rotation rate. This shall includelow AOA departure resi stance testing at AOAS between O and 15 degrees andhigh AOA hang-up testing. The objective and the maneuvers that shal 1 beperformed are 1 i steal in Table 111A.

3.3.4 .1.1 Fliaht simulation oroaram. Prior to flight testing forthe buildup program, a computer analysi s/ground based flight simulationshal 1 be conducted to:

a. Determine the high AOA character sties.

b. Investigate the ful 1 spectrum of possible maneuvers and controlinputs under all flight conditions.

c. Establish those maneuvers and control inputs that are notpossible to flight test with a reasonable degree of safety.

d. Evaluate coupling effects to establish critical control inputsand body rate combinations.

e. Produce an initial flight test plan.

This simulation effort, where feasible, should include pilot-in-the-loopand should incorporate the effects of rotary derivatives obtained fromwind tunnel testing.

3.3.4 .1.2 Fliaht test verification croaram. Flight tests shall beperformed to verify the analysis/flight simulation results. The generalguidelines for buildup maneuvers are listed in Table 111A. Once asatisfactory level of correlation has been achieved, the flight testprogram should proceed to establish, in safe increments, the mostcritical parameters. During the flight verification program, the flightresults shall be used to continually update the analysis/flightsimulation data base, ensure flight safety, and make efficient use offlight time.

32


MIL-D-8708C(AS)

-~

rest

a

b

c

d

TABLE 111A. Hi qh anal.? of attack bui id-up tests.

2

Name

Iigh angle of attacknvestigationgear UP)

Iigh angle of attacknvestigationgear down)

3

Flight altitude

Erect

Vertical

Inverted

Erect

Description

Determine:

::

::

e.f.9.h.

;:

k.

1.

m.

Buffet onsetBuffet characteristics(build-up in buffet intensity,moderate buffet, limit buffet,maximum tracking buffet)Pitch control limitApproach to stallcharacter sti csStall/departure resistancePost stall/departure gyrationsIncipient spin characteristicsSpin characteristicsSpin recovery characteristicsControl effectiveness in fullydeveloped spinEffects of misapplied recovevcontrols in fully developed

;!~cts of aerodynamic surfacedeflection in fully developedspin (canards, speedbrakes,etc. )Effect of failure ofartificial out-of-controlwarning systems or specialflight control law modes onspifi recovery.

Fully developed 5 turns erect(3 turns inverted) spin shallbe demonstrated holdingcritical pro-spin controls.

Same as above except terminateinvestigation when post stall/departure motions develop intothe incipient spin phase.

NOTE: The high angle of attack build-up and demonstration testsshall include the effects of:

Thrust levelSASICASDegraded orders in FCSStores configuration (symmetric andSpeedbrakeManeuver devicesCenter of gravityAltitude

asymmetric)

InertiaFailed aero surfaces (flight controls, flaps/slats,Transonic deceleration at elevated g

etc. )

33


L

rest

e

2

Name

Aggravated input

TABLE 111A. Hiah anale of att~-u D testJ - Continued.

3

Flight attitude

Erect

Vertical

Inverted

Erect

Vertical

Inverted

4

Angle of attack

lG Trim a to max AOA or+NZI imit whichever isless

As requi red

lG Trim ct min AOA or

-Nzlimit whichever isgreater.

lG Trim a to max AOA or~,

::Z ;~: : whichever

As requi red

-lG Trim a to a min or-Nzlimit whichever is

greater.

5

Description

!Building up in AOA and Mach to limiting conditions,perform the following full control step input$. ”ateach AOA:

a.b.c.d.e.f.

9.h.i.

j.k.1.

LateralLateral and aftLateral and fotwardLateral and rudder (coordinated)Lateral , rudder and aft (coordinated)Lateral , rudder a“d forward (coordinated)Lateral and opposite rudder (cross controls)Lateral , opposite rudder and aft (cross controls]Lateral , opposite rudder and forward(cross controls)Rudder controlAft controlForward control

Above max stablized AOA, transient AOAS shallbe investigated building-up from smooth to abruptlongitudinal inputs.

Same as above except simulate engine failure duringeach of the above maneuvers and simulate enginefailure at each Mach and angle of attack testcondition with controls neutral Since throttlemovement during post-stall gyrations or spins maybe detrimental to the engine operation, thethrottles shall be positioned prior to maneuverentry for power or asymmetric thrust effects.


uLrl

TABLE 111A. ~iah an~ build-n te* - Continued.

1“ . . c1 L > .

est Name Flight attitude Angle of attack Oesc.iptionI

f Coupling [kinematic Erect lG Trim a to uax AOA or Repeat all 2 and 3 axis aggravated control !:and inertia) +NZIimit whichever is

less.i r,put maneuvers, phasing control inPutSas rates peak about the first axis.

Establish max roll rate and apply thefollowing full control inputs: (uselateral control input for c. through h. androll with rudder for 1. through n.

Forward;: AftJertfcal As r.au~ redc. Rudder with

Inverted -lG Trim a to a min or d. Rudder against-$4Zlimit whichever is e. fotward and rudder w! thgreater. f. Forward and rudder against

9. Aft and rudder withh. Aft and rudder, againsti . Lateral withj. Lateral againstk. Fo~ard and lateral with1. forward and lateral againstm. Aft and lateral withn. Aft and lateral against

Establish ma. yaw rate and apply thefollowing full control inputs:

a. Forward e. Forward and lateral withb. Aft f. forward and lateral againstc. Lateral with g. Aft and lateral withd. Lateral against h. Aft and lateral against

Establish max nose down pitch rate and applythe following fuil control inputs:

a. Lateral c. Lateral and rudder (coordinated)b. Rudder d. Lateral and rudder [cross COntrOl )

Establish max nose up pitch rate and apply thesame.


MI L-D-8708 C(AS)

3.3.4.2 Fliaht demonstration tests. The flight demonstration shallconsist of Flying Qualities and Performance (FQ&P), high AOA, and spintests.

:3.3.4.2:1 Performance tests. The performance guarantee itemsspecified in the detai 1 specification shal 1 be demonstrated.

3.3.4 .2.1.1 Draa measurements. Hith the approval of the acquiringactivity, certain of the requirements of 3.3.4 .2.1 may be satisfied bymathematical formulation using flight data for the variation of dragcoefficient with 1 ift coefficient and instal led engine performance atsubsonic, transonic and supersonic Mach numbers, as appl i cable. Theseinflight aerodynamic and thrust measurements shal 1 be combined withappl i cable aircraft weight, center-of-gravity, and fuel volume tocalculate conformance with the performance guarantees specified in thedetail specification. Performance data requirements proposed forsubmittal by this method shal 1 be specified in the Performance OataReduction Report along with the detai led procedure to be used.

3.3.4 .2.2 Hiah AOA fliaht test variables. Tolerances for criticalparameters used to determine acceptabi 1 ity of demonstration maneuverssuch as Mach number, AOA, normal acceleration, and altitude shal 1 beestabl i shed by mutual agreement between the contractor and the acqui ringactivity prior to performance of the demonstration tests.

3.3.4 .2.3 Natural stall warning. The demonstration shal 1 establishi f natural stal 1 warning meets the requirements of MI L-F-8785 asspecified in the detail specification.

3.3.4.2.4 Artificial St all warning. When installed, artificialstal 1 warning shal 1 be demonstrated to meet the requirements ofMI L-F-8785 as specified in the detail specification. The flight test shalldemonstrate that:

a. The output fram tactile stall warning devices, such as stick orrudder pedal shakers, is not masked by airframe buffet or flightcontrol system dynamics and is readi ly discernible with the bodyin any normally anticipated position.

b. Visual stall warning devices are readily discernible nearperipheral vision limits, for any normally anticipated headposition, during day or night operation.

c. Aural , stal 1 warning signals are easily distinguishable fromgear, flap, and other malfunction tones or other aural signalsand do not block voice communication channels.

3.3.4 .2.5 Natural loss-of-control warninq. The effectiveness ofnatural loss-of-control warning or indication shal 1 be demonstrated.

3.3.4 .2.6 Artificial loss-of-control warninq. If artificial loss-of-control warning or indication is provided, it shall be demonstrated tobe effective in al lowing the pi lot to prevent departure.

36


MI L-D-8708 C(AS)

3.3.4 .2.7 ~. When aloss-of-control prevention device is required by the detai 1specification, it shall be demonstrated that the device effectivelyprevents departures under critical combinations of test parameters andmaneuvering circumstances.

3.3.4.3 SD ecifi c test reaui rements. After completion of the buildupprogram, the final critical demonstration conditions for the FlyingQualifies and Performance (FQ&P) and high AOA and spin demonstrationshal 1 be recommended by the contractor at the High AOA and SpinOemonstration Conference. The final critical points to be demonstratedare as li steal in Tables IIIB and IIIC respectively. Approval of the flighttest program shal 1 be obtained from the acqui ring activity prior to thestart of the formal demonstration.

3.3.4.3.1 Out-of-control recoverv Drocedure. When an aircraft issubject to departure from control led flight while performing the high AOAflight test, the out-of-control recovery procedure shal 1 be demonstrated.Such a recovery procedure should not require the pi lot to determine thenature or the direction of the post-stal 1 motion in order to properlyexecute the recovery steps. Other recovery procedures shal 1 berecommended, as required, for an aggravated departure, deep stal 1condition, erect spin, or inverted out-of-control events. The altitudeloss values, associated with the out-of-control events, shal 1 also bedetermined and compared to simulation predictions. It shal 1 be determinedif the aircraft is subject to any appreciable recovery-inhibiting effects.

3.3.4.3.2 s~ verv-Cl a I and IV ai rcra When a departurefrom controlled flight or a deliberate spin attempt ~esults in a spin whileperforming the high AOA flight tests, a satisfactory spin recoverytechnique shal 1 be demonstrated. Turns for recovery shal 1 not exceed thosespecified in MI L-F-B785. Under normal application circumstances, therecovery procedure should not subject the aircraft to spin reversals or achange of spin mode that prolongs recovery. The spin recovery procedureshal 1 be compatible with the out-of-control recovery procedure with aminimum of changes or additions. Accompli shment of the recovery procedureshould not be compromised by accelerations at the crew station. Controlforces shal 1 not exceed those values specified in MI L-F-8785. For ClassIV aircraft, with fly-by-wire and advanced cockpit di splays, the fol lowing

“demonstration requirements apply:

a. Engagement/disengagement thresholds of manual automatic spinrecovery flight control modes shal 1 not inhibit or preventrecovery fram out-of-control flight conditions.

b. Cockpit displays shall always present correct information to thepi lot for recovery from out-of-control flight conditions. Spinrecovery procedures shal 1 have a minimum of changes or additionsfor all configurations and loadings, including asymmetricexternal store laadings.

37


TABLE 1110. Flvin.a au alities demonstration test~.

ThrustTest

(11—

(2)—

,(3)—

.(4)—

l(l)—

)(2)—

I(3)—

1(4)—

:(1)—

c(2)—

C(3)—

c(4)

1 ti tude(feet)

A/conf i g

PA

Storeconf i g

Cl em

Grossweight

.OGU

descriptionName

Static longitudinalstabil i ty

C.G. Speed

longitudinal stick forces, stick>ositions, and control’ surface]osi tions required to qaintainIpeeds both lower and higherthan trim speed shall bedemonstrated. Flight pathrtability data shall bejetetmined. Data shall beicqui red utilizing the stabilizeJoint technique or the accel/jecel method,

rhe elevator control .forces,stick positions, and controlsurface positions versus loadfactor shall be acqui red up tomzm x Utili Zin9 steady and wi”d-

?up urns.

‘t limitPAmin

; 5000 ft LF

Critical

Crt Clean :ritical :ritical ritical

Critical

Manwveri ng1 ongi tudi na\stability

CR Clean

Critical

;ritical Ft limit jritical ri tical ,s reqd

Clean

Critical

d limit

Groundlevel

is reqd lhe minimum speed at whichtakeoff attitude can be attainedand maintained shall bedemonstrated frun brake rel easein configuration TO and frOM a4 degree gl ideslope inconf i g“rati on 60.The requi red cant rol forces shal’be recorded throughout thetakeoff and acceleration to1.3 V to without change inthrust, trim, gear, or flapsetting. Overrotation tendencieshall also be investigated.

Nosewheel li f t-off To Clean

Critical

Critical Critical is reqd

00 Cl em LOGW

Critical


d

e(1)

e(2)

‘?(3)

e(4)

f

Ground effecthold-off

Longitudinal controlforces in dives

Trim changeduring wave-off

TABLE IIIB. Flyinq a ual ities demonstration tes Q - Continued.

A/Cconf i g

L

(S% in)

CRS/B out)

(S?1 in)

CRS/B out)

PA

Storecon fig

Critical

Clean

Critical

Critical

Grossweight

Critical

Critical

Critical

C.G

Criticalfwd

Max fwd

Critical

Speed

vPAmi n

Critical

4PAmi n

A1 ti tude(feet)

Groundlevel

h reqd

< 1000 fliL

Thrust

W?

As reqd

TNA

Description

The minimum speed attainable inground-effect and ttie 4 tickforce requi red to maintain therequi red elevator deflection atthis speed.

Determine the magnitude and rateof change of longitudinal controlforces in dives to maximum ai r-speeds, and the ease with whichthese forces can bp maintainednear zero by retrimming. Withairplane trimmed for level flightand without changing power,except as requi red to preventexceeding VL the ai rpl ane shallenter and ma{ntain a 70 degreedive or a dive angle corres-ponding to max permissible air-speed, whichever is less, tominimum safe al ti tude for pulloutand recovery at not less than3g. The maximum longitudinalcontrol force requi red at maxairspeed shall be noted through-out the dives with and withouttrimmings.

With the ai t-plane trimmed on a4 degree gl ideslope inconfiguration PA, perform thechange to configuration hU andmaintain the original approachangle-of-attrack. Thelongitudinal control forcerequi red to maintain this AOAshall be shown.


TABLE 1110. ~ration tm - Cent i nued,

Test Namestorecon fig

Grossweight

Altitude(feet)

A/Cronfig C.G. Speed Thrust Description

g(l)

g(z)

;peed brakeeffectiveness

CR Critical Critical Critical Critical

‘H

25CI KIAS

Critical

Critical Critical Investigate effectiveness ofspeed brakes. Detetmineelevator force requi red tomaintain same point of aim andthe normal accelerationObject ional trim changes,buffet, or other characteristicsshould be noted.

Cl em 25,000 ft IRT Oetermine the time requi red todecelerate the airplane frommaximum level fl ight ai rspeed(VH) at the specified powersetting to a speed 80% of thatspeed using the decelerationdevices(s). Engine thrust shal 1be reduced from lRT to a levelwhich lRT can be obtained in notmore than 5 seconds.

As the specified airspeed, thetime of descent shall bedemonstrated on an on-coursedescent from 25,000 ft to 5,000ft with throttle at idle.

Determine short period frequencyand damping as wel 1 aslongitudinal accelerationsensitivity (nZ/a) . Utilizeboth longitudiml stick doubletsas well as stick raps (pulses).Loo period characteristic cs

7sha I also be determined forconfigurations CR and PA.

9(3) Idle

As reqdh(1)—

h(2)

lynami c lo”gi tudi”alstability

CR Clean

Critical

Critical ft limit Critical

h(3)

h(4)

PA Clean

Critical

. 5000 ftS1


TABLE 1118. Flvino au alit{es demonstration test s - Continued.

mConf:g

CT

Storeconfi g

Grossweight

;ritical

:ritical

Altitude(feet)

- 5000 {SI

Critical

As reqd

Critical

rest Name

h(5)

h(6)

i(1) Pilot-induced_ oscillations

i(2)

i(3) In-flightrefueling

i(4)

i(5) Air-to-air tracking

C.G.

Ft limit

Critical

Speed

:ri tical

:ritical

IS reqd

Thrust

is reqd

Critical

ks reqd

description

Cl ea.

Critical

CriticalPA rhe contractor shall fly the!irpIane in flight conditionshere PIO tendencies about all!xes are predicted. Hightorkload mission tasks shall be~lovn to expose PIO tendencies.accumulate sufficient flighttest data to detemnine whetherI tendency exists for divergentar uncontrollable oscillationsto occur from pilot inputsjuring high pilot workloadsituations. Sinusoidal controlinputs shall be utilized fortests i(1) and i(2) to determineif PIO tendencies exist. The:ri tical tanker shall be usedfor in-flight refueling.

CR

PA

CR

ai(6) [ Air-to-ground tracking

PA

3+== CR Clean :ritical

Determine the r~dder positi?n,rudder force, a)leron posit> on,aileron force, bank angle, andsides lip UP to full rudderpedal application or aileronlimit using steady headingsides lips,

j(l) Static lateral-directional stability

j(z)

j(3)

PA Cl ea.

Critical

Critical Critical critical I = 5000 I1s1

As reqd

CR Clean Critical


r–

II

TABLC IIIB. ~,tlm ,. - Canti”ued.

—

estA/c

:onf igStorecon fig

Grosswe! ght

,1titude{feet)Name C.6, Speed Thrust Description

(4)—

:(1)

CR Critical :ritical .ritical :ri tical :ritical As reqd

)ynamic lateral-~irectionalstability

PA Clean jritical ‘t limit :ritical = 5000 ft1

;ri tical

Determine the spiral mode.Determine the Dutch Rollfrequency and damping uti 1 izi ngthe rudder doublet technique.

:(2)—

:(3)

Critical

CR Cl ea.

As reqd

‘Critical((4)

111) ‘PAmi n-5Roll performance and

lateral controlsensitivity

PA Clean Critical ;ri tical ❑ 5000 ft;1

Determine the bank angle achiev-able in one second, steady stateroll rate, rol 1 mode time.constant, roll rate oscillationparameter (Pose/Pavg, bank angleoscillation parameter(@.C/$avg), and sideslip

‘xc”’””” ‘arm’’” ‘A%’K” “Adverse fpro.+erse yaw ten enc>esshal 1 be noted. Rudder pedalsshall be held fixed or free ifnecessary to denm”stra$lanyof these parameter.control forces. positions. anddisplacements shal 1 be shown.In the case of asyimnetri cstores, the demonstration shallbe performed rolling into theunloaded win$. ?ests shall beperformed utillz)ng bank to bankfull lateral stick deflectionrolls. Lateral controlsensitivity shall @lso beinvestigated.

Critical1(2) TO

Criticalasymnetri t

‘PAmax


Mon fig

TABLC IIIB. flyino 0“ ~ - Continued.

Storecon fig

Grossweight

\ltitude(feet) descriptionTest I Name C.G. AOA Speed rhl-ust

m(1) Rol 1 performance andlateral controlsensitivity

CR 1ean :ritical ,ri tical :ri tical ,$ reqd Low rLF ‘or wings 1 evel ,,fl ight,Ietermine bank angle in one ~~iecond, time to .$0 degrees bank:hange, rol 1 mode time constant,;teady state roll rate,%sclPa.g, @c/..$avg ABmax/k,idverselproverse yaw tendenci es:ontrol harmony and COUP1 ingMIdencios from Ig wings level ,~ull deflection rolls and fromjreater than lg flight..ateral control sensitivityshal 1 also be investigated. Thestores configuration shallinclude a critical asymmetrictxternal loading.

m(2)—

m(3)

ritical

1ean

ri tical

Hed

m(4)

m(s)

m(6)

:1ean

:ri tical

Hi

n(1) IAsymmetric thrust(in-flight)

TO/CR

PA

:ri tical :ri tical :ri tical Critical’ is reqd ❑ 2000 f!GL

Criticieng cut

Determine ❑inimum trimairspeeds: static and dynamicninimum control airspeeds;approach, landing and waveoffflight characteristics: safetyspeed on takeoff; and flyingqual i ties characteristics forlong range cruise tasks withasymmetric power. No correctiveaction should be taken unti 12 seconds after the criticalengine is cut or 20 degrees ofbank. The minimum airspeeds atwhich the a{ rplane is safelycontrollable throughout theensuing motions and. fol lowingtransients, at which the rudderand ai Ieron are capable ofholding the airplane to zeroyaw and roll rates with not morethan S degrees of bank angleshall be demonstrated.

n(2)

n(3)

n(4)

n(S)

la

CR Critical

00


.

Test

0

TABLE 111 B. Flvinq aua lities demonstration test - Continued.

Name

isynnetric thrust~ground)

A/cconf i g

TO

Storeconf i g

:ri tical

Grossweight

Critical

C.G.

:ri tical

Speed

Critical

Altitude(feet)

Groundlevel

Thrust

Criticalenginecl! t

Description

Oetennine the static aiddynamic minimum control, groundspeeds (the dynamic tests shouldonly be conducted if sufficientanal ysis and build-up testspredict an acceptable degree ofsafety); determine the maximumairspeed that can be acceleratedto, lose an engine and stillmaintain control of the ai rplanewith no more than 30ft deviationfrom runaway. centerline. Oeter-mine dynamic abort character-istics utilizing normal abortprocedures as determined by thecontractor. Tests with andwithout nosehlml steeringengaged should be conducted i fapplicabl e.. NO corrective actiorshall be taken unt~l 1-2 secondsafter the engine is cut or until30 ft of deviation from runwaycenterline is exceeded, whicheveroccurs fi rst and is the mostcritical element in the test.


TABLE IIIB. Flvina w alities demonstration tests - Continued.

:est I Name

d Asymmetric thrust

—

q(1)—

q(2)

Asymmetric storeconfigurations

A/Cconf i g

Critical

PA

CR

Storecon fig

:ri tical

Criticalsymnetry

Grossweight

:ri tical

Critical

C.G.

critical

Critical

TAltitude

Speed (feet)

;ritical Critical

:ritical 1.10,000 f!

Thrust

Critical

Critical

Description

!,”

rhe minimum speed for a,safedescent, approach, and 1 andingshall be demonstrated wi th asimulated engine seizure ataltitude. Seizure may besimulated by permitting theseized engine to windmill ;however, the effects of thetiindmill ing engine on the powercontrol system shal 1 beeliminated by means of a cockpitcontrol or otherwise at the timeof simulated engine failure andthis condition shall bemaintained until the landing hasbeen completed. Trim changesduring configuration changesshall be noted.

Oetennine the min$mum trim andminimum safe airspeeds. Noteany objectionable flyingqualitles characteristics.


TABLE IIIB. Flyin.a Qua lities demonstration tests - Continued.

A/C:onfig

Storecon fig

Grossweight

klti tude(feet)Name C.G. Speed Thrust Description ,.

Hinimum control airspeeds andflight characteristics shall bedemonstrated for criticalmoveable aerodynamic surfaceasyninetrics as well as safedecent and 1 anding fromaltitude, if these asymnetricsare probable failure modes inflight control system.

r(1) \symemetri c movableaerodynamic surface

PA

CR

CR

Clean

Critical

Critical Critical Critical - 5000 f51

Critical

4s reqd

As reqd

Critical

r(2)

r(3) NOA

Cleanr(4)

r(5) Critical

r(6) NOA

rransonic flyingquali ties

s(l)—

S(2)

—

t(1)

Clean Critical Critical 4s reqd Investigate level flight accel/decel characteristics with andwithout speedbrakes. Stabilizeat predetermined Mach numbers intransonic region and investigatetrimnability about all axes,short period characteristics,P1O tendencies, longitudinalmanuevering stability, lateral-directional stability, rollperformance and lateral controlsensitivity. Investigatelongitudinal characteristicsduring high g decelerationthrough the transonic region.

Critical

Stability/controlaugmentation

PA Clean

Critical

Critical Critical Critical Critical As reqd Demonstrate the flying qualitiesfor single axis failure of theSAS and CAS systems. Airplanecontrollability at the time ofeach failure shall also bedemonstrated allowing for apilot reaction time.

t(2) System failures(SAS/CAS)

(Continued on next page)


a.4

TABLE IIIB, Flvin.a Qual ities demonstration test s - Continued.

A/C Store Gross AltitudeTest Name conf i g con fig weight C.G. Speed (feet) Thrust Description

t(3) CR Clean Critical Critical Critical Critical As reqd (Continued from previou~ page)flight control system designed

t(4) Criticalto operate with both US and

Critical CAS on or off only, whereindividual operation of theW or CM is not possible,shall be demonstrated withsingle failures of the pitch,roll, and yaw axes. In both’ ~control systems, flyingqualities will also bedemonstrated with SM/CAS off.

u(1) Back-up flight PA Clean Critical Critical Critical h-1000 ft Critical On airplanes equipped with acontrol systems AGL back-up flight control system,

the flying qualities shall beu(2) Critical demonstrated with only the

back-up flight control system

u(3) CRin operation. These tests shall

Clean Critical include a demonstration of:

field landingu(4) Critical ~: controllability about all

axesc. recove~ from unusual

attitudesd. ;;M:bty to control rate of

e. ability to perform moderateroll rate bank to bankmaneuvers

f. ability to perform point topoint navigation maneuvers.

v(1) Crosswind takeoffs and TO Clean Critical Critical Critical Ground AS reqdlandings

Oetennine crosswind limits forlevel takeoffs and landing without

the use of differential braking.v(2) Critical

V(3) PA Clean

v(4) Critical

v(5) Criticalasvmnet ri c


——

TABLE 1116. Flvina au al itie s demonstration tests - Continued.

NOTES :

(1) @itical, when it appears as the only store configuration for ? 9ive~ test, shallInclude consideration of the clean airplane as a possible configuration.

(2) From toe avai I able buj 1 -up and fl igh demonstration data. for1 fdeterm!ng. where posslb. e, the neutra and maneuverln9 Points %t~o!ha!~~~,ean

and crltlcal store loadlngs.

(3) ~~~[~g~~ationnormafRLrl![$h~s!!l~~ses power ~ettlng wi?[ be as speci!~ed In table

of this tqble, r ers only to Far UP and

~ “} app{tcab!e.and wil] include augmen ed hru~ if val I able.transonlc and supersonic, 1

Critical airspeed shall Include

(4) Configurat~on PA for the purposes of this table, refers to al 1 power approachconfigurations tkat the airplane shal 1 fly.

(5) Configuration NOA for the purpos?s o[ ~!ij!ronmeni.

“ table refers to normal operationalasymnetrles expec{ed In an operatlona

(6) Minimum $afe airspeed is the minimum @irspeed that the airplane can be flownsafely with pilot control o ces requlr~d to malntaln straight and level flight.

[!Th\s speed W111 be below m n mum trim a~rspeed.

.


TABLE lIIC. Hiah angle of at tack demonstration tests.

restFlight

NameStores

attitude Mach AOA confi g C.G. Thrust Description

b High angle of attack As reqd Critical Critical Critical!

Critical Criticaldemonstrations manuevers

The following final criticalmanuevers shall be demonstrated:

a. Erect lg stall (cruise andhigh lift configurations)=

b. Erect accelerated stall(cruise and high liftconfigurations)”

c. Inverted (-lg) stalld. Inverted accelerated stal 1e. Erect aggravated input

departure (cruise and highlift configurations)

f. Inverted aggravated inputdeparture

g. Erect coupled departureh. Vertical stall (tail slide)i . Vertical aggravated input

departurej. Erect spin from lg entryk. Erect spin from accel crated

aggravated entry (cruise andhigh life configurations) “

1. Erect spin frun inertiacoupled entry

m. Erect spin from verticalentry

n. Inverted spin from -lg entryo. Inverted spin from

accelerated aggravated entryp. Inverted spin from inertia

COUP1ed entryq. Inverted spin from vertical

entryr. 10 additional manuevers

tailored to the mission andconfiguration (aerodynamic,flight angle-of-attackcontrol systems, thrust,etc. )

- Post stall gyration only isto be demonstrated


MI L-D-8708 C(AS)

3.3.4 .3.3 Ermine oDeratina characteristics Engine operatingcharacteristics shall be documented while perfo~ming the flight testbuildup and demonstration. If engine stalls are not prevented, clear andunambiguous cockpit indications of impending or actual stall , flameout or

over.temp, and identi fi cation of the malfunctioning engine(s) shal 1 bedemonstrated at high AOA/sideslip out-of-control f light condi tions unless

automatic stal 1 or overtemp protection logic is incorporated in theengine control system(s). When engine malfunction occurs during high AOA

flight, it shal 1 be demonstrated that recovery from the existing orensuing out-of-control mode(s) can be accomplished at least 10 secondsprior to the projected time at which loss of abl lity to position the

flight controls would occur due to the engine malfunction. This

requf rement shal 1 be met with the throttles remaining in the leastconservative position.

3.3.4.3.4 Recoverv characteristics. ‘Recovery dynamics and maximumeffort dive pullout characteristics shall be thoroughly determined.Altitude loss i n out-of-control events and total recovery altitude valuesshal 1 be recorded over a wide range of out-of-control maneuvers and storeloading. Steep rolling maneuvers and erect and inverted spirals shall beexamined to determine i f these motions may appear similar to out-of-control or recovery events. When potential misinterpretation of themaneuvers can 1ead to improper control application, al 1 cues to the pi lotthat will al low proper recognition shall be identified.

3.3.4 .3.5 Traininq maneuvers. Flight training maneuvers:appropriate to the aircraft Class and mission, shall be identified toillustrate the high AOA flight characteristics. Inverted flight shal 1 beincluded as requi red. The procedures for performing these maneuversshall be clearly defined so service pilots can safely practice themaneuvers. Specific guidelines concerning the type of training maneuversmay also be provided by the acquiring activity.

3.3.4 .3.6 Baseline stabilitv a nd control tests. When it isanticipated that special modifications may significantly alter the basicproperties of the test aircraft, high AOA, longitudinal , and lateral-directional stability and control flight tests shall be conducted earlyin the demonstration program, within the established safe limits. Testresults shal 1 be compared with simi lar data from a production configuredaircraft. Specific guidelines concerning the types and conditions forstability and control flight tests to be performed may also be providedby the acquiring activity.

3.3.4.3.7 Qualitative so in dtY.CriDt ion. Spin mode modifiers forqualitative description of a spin are listed in Table IV.

3.4 Propulsion Sv stem demonstration.

3.4.1 Propulsion svstem tests. None of the tests specified hereinshal 1 be construed to require operation of the aircraft under conditionswhich would exceed safe operating limits established in the flight clearanceissued by the acquiring activity. The propulsion system demonstrationdoes not necessarily require a dedicated aircraft. If otherdemonstration aircraft have the necessary instrumentation installed,propulsion system demonstration tests can be “piggy backed” on othertests. The definition of power is contained in section 6.

50


MI L-D-8708 C(AS)

TABLE IV. sin mode modifiers.

Sense Attitude Rate Oscillations

Erect Extremely slow Smoothsteep

Inverted Steep Fast Mi idlyosci 1 latory

Flat Extremely Osci11 atoryrapid

Highosci 1 latory

Violentlyosci 1 latory

51


MI L-D-8708 C(AS)

3.4.2 Aircraft configuration. Except forflight test vehicle shall be representative ofal 1 significant respects. Both the enqine and

the instrumentation, thethe production aircraft inaccessories. such as fuel

control and afterburner, shal 1 be the ~odel proposed for the productionaircraft. The airframe/engine installation, including inlet ducts, shallbe that proposed for the production aircraft. If the aircraft to bedemonstrated includes an automatic or manually variable inlet geometrysystem, the equipment shal 1 be functioning throughout the demonstrationprogram.

3.4.3 Fliqht test instrumentation. Instrumentation shall beprovided in accordance with the Demonstration Instrumentation Report.

3.4.3.1 ~. Instrumentation shall beprovided to measure thrust using a calibrated thrustmeter or bymeasurement of the change in momentum of the air passing through theengine. Static and total pressure at the compressor inlet and totalpressure at the turbine outlet shall be measured. Engines installed incarrier aircraft, where there is a possibility of steam ingestion fromthe catapult and/or exhaust gas ingestion from the jet blast deflector,shall have instrumentation installed necessary to detect inducedcompressor instabilities. If an automatic or manually controlledvariable inlet geometry system is instal 1 ed, instrumentation shal 1 beprovided to indicate and record the geometry position during alloperations.

3.4.3.2 TurboDroo and turboshaft enoines. Instrumentation shal 1consist of a torquemeter to measure power and the necessaryinstrumentation to determine thrust by measuring the change in momentumof the air passing through the engine at the same time. Static and totalpressure at the compressor inlet and total pressure at the turbine outletshal 1 be measured.

3.4.3.3 Rocket. ram-i et. and DU 1 se-iet enqines. Rated thrust outputshal 1 be measured using a cal ibrated thrustmeter.

3.4.3.4 Prooe 1 ler driven aircraft. Suitable instrumentation shallbe provided to CO1 lect vibration and stress data on the propeller asinstalled on the engine.

3.4.4 Contractor demonstration reoui rements. The propulsion systemdemonstration shall consist of:

a. Buildup tests to characterize the airframe/propulsioninstallation.

b. A formal ground and flight demonstration to determineperformance character sties of the i nstal led engine.

3.4.4.1 Build-uD t est Droaram. Prior to commencement ofpropulsion systems demonstration, a build-up program shall beconsisting of a vibration survey, a installation temperature survey, acompressor inlet and turbine outlet pressure survey, and a propellervibration survey (for propeller driven aircraft).

the

the formalconducted

52


MI L-D-8708C(AS)

3.4.4 .1.1 n iE u ne vfbratlon survey F1 !ght and ground tests shal 1 beconducted to collect vibration data on”the engine lnstallat!on andsubstantiate a satisfactory installation. Vibration data shall beprov~ded to the engine manufacturer for use i n determ!nlng If vibrationsof. the airframe and engine combination affect the engine. The surveyshal 1 fnclude an evaluation of the structural integrity of the engine,drive train (if applicable), and the airframe. Structural fatigue of theprime load paths to and through the engine, and vibration character stiesof the engine and its installation at frequencies corresponding to eachforcing frequency shal 1 be determined. Although the prime contractorshall be responsible for the collection and submittal of all enginevibration survey data, the engine manufacturer may participate in thedetermination of instrumentation and test procedures to be used for thissurvey. Analyses of the data for specification compliance, with proof-of-design of airframe, installation components, and engine componentsshal 1 be prepared by the airframe and engine manufacturers respectively.Release for first flight and for OT-11 shall be contingent onsatisfactory ground and flight vibration surveys respectively. Enginestress measurements, if requi red, shal 1 be recorded during the vibrationsurvey(s).

3.4.4 .1.2 Enaine l.rdal lation te Derature survey Ground and flighttests shal 1 be performed in accordanc~ with MI L-C-8678 to demonstratethat the engine installation meets the specified temperature 1 imitations.

3.4.4.1.3 essor inlet and turbine outlet ore~e surveyturbojet, turbofan, turboshaft, and turboprop engine installations: a

On

static and total pressure survey at the compressor inlet shal 1 beperformed. A total pressure survey at the turbine outlet shal 1 beperformed. These surveys shal 1 be made throughout the maneuveringenvelope of the aircraft to define distorted flow conditions. Inlet airpressure variation shal 1 be determined in accordance with MI L-E-5007 ateach of the test point condi tlons and compared to the recotmnended valuesin the engine model specification. If the measured values exceed theengine model specification maximum tolerable values, this discrepancyshall be reported to the acquiring activity.

3.4.4.1.4 ProDel ler vibration survey For propeller drivenaircraft, ground and f 1 ight tests shal 1 be conducted in accordance withthe vibratory stress survey requirements of MI L-P-26366. The aircraftmanufacturer shal 1 provide the necessary equfpment and personnel for datacollection. The propel ler manufacturer WI 11 prepare the required data onthe propel ler-stress survey. If the propel ler-vibration-s tress surveyindicates unsatisfactory vibration stresses In the propeller, theacquiring activity w1ll place the responslb!llty for correction of thiscondition in each specific case, and the tests shal 1 be repeated todemonstrate correction of the unsatl sfactory character sties.

3.4.4.2 Prcmul sion svstem around and f 1 iaht demonstrations Forma 1ground and f 1 ight demonstrations shal 1 be scheduled fol lowing theanalysis and approval of the data from the bui Idup test program. Thesedemonstrations shall consist of:

a. Demonstration of engine character sties during ground operatton.

b. Demonstration of engine characteristics in flight.

53


MIL-D-8708C(AS)

c. Engine power output runs.

d. Mi 1 itary power runs.

e. Propeller operation (if applicable).

f. Fuel system demonstration.

3.4.4 .2.1 Demonstration of encsine characterlsti [s durinq qroundoDeration. During ground demonstrations, the power output and thrustmeasurements specified for the applicable tests of paragraph 3.4.4 .2.3shal 1 be recorded. It shal 1 also be demonstrated that the thrustavailable at idle RPM does not cause excessive taxi speeds. Foraugmented engines, the fol lowing measurements shal 1 also be obtained.

a. Fuel mani fold pressure.

b. Fuel flow.

c. Fuel pump discharge pressure.

3.4.4 .2.1.1 St arti nq character sties. Measurements shal 1 berecorded at intervals of O. 1 seconds for al 1 starts except cross startswhere intervals not to exceed 0.2 seconds are acceptable. On enginecontrol systems which uti 1 ize digital inputs and outputs, the datarecording shal 1 be consi stent with the system uDdate rate: however. theupdate rate shal 1 be greater than 10fol lowing data shal 1 be recorded for

a. Time.

b. Engine speed.

c. Engine ‘temperature.

d. Starter voltage.

e. Starter current.

f. Power source(s) voltage.

9. Power source(s) current.

measurements per second. Thestarting character sti CS:

The fol lowing starts shal 1 be performed:

a. For automatic control systems, three starts shal 1 be made ‘inaccordance with the engine manufacturer’s starting procedure. Onmulti-engine aircraft, the three starts need only be made on theengine(s) on one side except that all engines shall be started atleast once.

b. If an emergency control system (manual or electrical) isprovided, two starts shal 1 be made on the control in accordancewith the engine manufacturer’s specified procedure. On multi-engine aircraft, two starts need be made only on the engine(s) onone side.

54


MI L-D-8708 C(AS)

c. If a cross starting capability is provided, two starts on thesecond engine shal 1 be conducted using the aircraft DCgenerator(s) or converter(s) power assi steal by the aircraftbattery (ies).

3.4.4 .2.1.2 ead~.s When 1 ever settings onthe primary control and on the manual (emerge~cy) control are provided,tests of the lever setting shal 1 be performed for turbojet, turbofan,turboprop and turboshaf t engines at:

a. Idle.

b. 50 percent intermediate thrust/power.

c. 65 percent intermediate thrust/power.

d. 90 percent intermediate thrust/power.

e. 100 percent intermediate thrust/power.

f. 100 percent intermediate thrust/power to maximum thrust/power ifapplicable.

9. Minimum booster engine power.

h. Maximum booster engine power.

Measurements shal 1 be recorded at five second intervals. Tests shal 1 beof four minutes duration after reaching the specified power ratings ateach control lever setting. A minimum of five measurements, to determinecontrol system transients, shal 1 be recorded for the first minute of eachtest after reaching the specified power ratings.

3.4.4 .2.1.3 Acceleration characte ristics. Slow, intermediate andsnap accelerations and decelerations shal 1 be performed with the primarycontrol. Slow and intermediate accelerations and decelerations shall beperformed whenever a manual (emergency) control is provided. Thefollowing accelerations, where applicable, shall be performed over thefol lowing ranges for turbojet, turbofan, high-bypass fan, turboprop andturboshaft engines:

a. Power approach to intermediate thrust/power.

b. Power approach to maximum thrust/power.

c. Idle to 100 percent intermediate thrust/power.

d. Idle to maximum thrust/power.

e. Maximum continuous to maximum power (A/B)

f. Intermediate to maximum thrust/power.

9. Minimum afterburner (A/8) thrust to maximum thrust.

55


MI L-D-8708 C(AS)

h. Minimum booster engine power to maximum booster engine power.

i. Throttle bodies (decel-accel ) at the most critical conditions.

On multi-engine aircraft, tests are required for the engine(s) on oneside. The test shal 1 be performed by starting with slow acceleration anddeceleration rates, then increasing to an intermediate rate, and thenincreasing to a snap rate (idle to intermediate throttle advancement inone second). The snap accelerations should be conducted i n steps fromengine idle to intermediate thrust and compared to the engine simulationmodel used for APC and ACLS system development. The steps should vary insize from approximately 200 lbs up to a value limited by the intermediateor idle steps. The steps should be initiated at approximately 10different thrust levels over the idle to Intermediate thrust range. Snaprate need not be performed with the manual control in tests d. , e. , f. ,g., and h. Parameter measurements shal 1 be recorded at 0.1 secondintervals, except on engine control systems that uti 1 ize digital inputsand outputs less than O. 1 second. In such cases, the data recordingshall be consistent with the system update rate. A minimum of 10measurements shal 1 be recorded to show control system transients for eachacceleration and deceleration.

3.4.4 .2.1.4 Noise level measurements.

3.4.4 .2.1.4.1 TurboDrous /turboshaft. With all engines operating atmi 1 itary rating, noise level measurements shal 1 be taken on the ground onone side of the aircraft at 30 degree intervals on 25, 50, 100, and 200foot radii , from 1 ines originating at the centerline of the aircraft inthe plane of the propeller. Test instrumentation shall be as listed inthe Demonstration Instrumentation Report.

3.4.4 .2.1.4.2 Turboiet/turbofan. Hi th al 1 engines operating atmaximum power, noise level measurements shall be taken at 12.5, 25, 50,100, 200 and 400 feet radii centered at the nozzle, or midway betweennozzles of the tai 1 pipes in intervals of 30 degrees around the aircraft.Test instrumentation shal 1 be as 1 i steal in the DemonstrationInstrumentation Report.

3.4.4 .2.2 Demonstration of enaine characteristics in fliaht.Measurements shal 1 be recorded at five second intervals during the testsfor accelerations and decelerations and afterburner operati on. A minimumof 20 sets of measurements (or sufficient data to show control systemtransients) for military power runs shal 1 be recorded on one engineduring the tests for acceleration, deceleration, and afterburneroperation for demonstration of al ti tude power control performance. Foraugmented engines, the fol lowing data shal 1 also be recorded:

a. Fuel manifold pressure.

b. Fuel flow.

c. Fuel pump discharge pressure.

56

!


MI L-D-8708C(AS)

3.4.4 .2.2.1 h nu mber climbs Three climbs shall beperformed at three different power lever settings, including intermediatethrust and maximum afterburning, at three different Mach numbers. Ninecl imbs shal 1 be performed from 2,000 feet pressure altitude to the combatcei 1 ing for each of the Mach number power lever setting combinationsselected. Where maximum aircraft Mach number is not achievable at 2,000feet, additional constant Mach number climbs at maximum power shal 1 beperformed at speeds increasing in 0.05 Mach number increments throughoutthe envelope of the aircraft. The climbs shall be initiated at minimumal lowable altitude for the particular speed and terminated at maximumpower combat cei 1 ing.

3.4.4 .2.2.2 ~. A low weeddescent from service cei 1 ing to 2,000 feet pressure altitude with powerlever in idle position (flight idle for turbojets and turboprops) shallbe performed. A level deceleration from max Mach to minimum airspeed for1 .Og level flight shall be performed with the power lever in the idleposition to demonstrate proper operation of the Mach-Idle airflowschedule. These decelerations shal 1 be performed at two altitudes thatal low for high Mach number operation.

3.4.4 .2.2.3 ~. Measurements recordedat no greater than 0.25 second intervals shal 1 be made for slow,intermediate, and snap accelerations and decelerations from 10,000 feetpressure altitude to mi 1 itary power service ceiling in 10,000 feetincrements for tests a. through e. below. Oata shal 1 be recorded duringthe stabi 1 ization period to document engine and control systemtransients. The flight parameters to be held constant during thestabilization period shall be specified in the Propulsion SystemDemonstration Test Plan. The fol lowing tests shall be performed:

a. Idle to 100 percent intermediate power or thrust (all engines).

b. Idle to maximum power (afterburner) (turbojet and turbofanengines).

c. Intermediate to maximum thrust (afterburner) (turbojet andturbofan engines).

d. Minimum afterburner thrust to maximum thrust (turbojet andturbofan engines).

e. One acceleration and one deceleration of the booster engine fromminimum rated thrust to full thrust at main engine, militarypower service ceiling (throttle movement during acceleration anddeceleration shall be compatible with engine limitations).

f. A simulated wave-off, from power approach thrust to intermediatethrust, shal 1 be demonstrated and recorded at a pressure altitudeof 5,000 feet.

9. Takeoff thrust transient shal 1 be demonstrated by performing asnap acceleration from idle to military power on an engine thatwas operated for 15 minutes at idle power at sea level staticconditions prior to the power advance.

57

I

I


MI L-D-8708C(AS)

A soak time of not less than 15 seconds for turbojet, turbofan andturboprop engines, shal 1 precede the power 1 ever movement foracceleration tests. A minimum of 10 measurements (or sufficient data toshow system transients) shal 1 be recorded on one engine during eachacceleration and deceleration test conducted during mi 1 i tary power runs.Fol lowing acceleration and deceleration, the engine power setting shal 1be retained unti 1 the engine has stabi 1 ized.

3.4.4 .2.2.4 Enaine stall checks. Engine stall checks shall beperformed from 10,000 feet pressure altitude to mi 1 itary service cei 1 ingin 10,000 foot increments. Five engine stal 1 checks at each altitudeshall be made by performing “bodie” and “reverse bodi e“ throttletransients at anticipated minimum stal 1 conditions. Prior to thesetests, the engine shall be stabilized at the condition(s) that Drovidethe most adverse engine operating state for engine stal 1 margin’. Thefive stal 1 checks at each altitude should be performed at evenly spacedintervals of airspeed from Vmin to Vmax. Stal 1 checks shall also be madeat the maximum allowable sides lip angles for assessment of inletdistortion effects. If electronic fuel control system stal 1 protectionlogic (active and inactive) is utilized, this system shall bedemonstrated.

3.4.4 .2.2.5 Emeraency D rotection. When an emergency control (manualor electrical) is provided, switchovers from primary control to emergencycontrol shal 1 be demonstrated during normal rated thrust or power levelflight runs at 10,000 feet intervals from 10,000 foot altitude to serviceceiling (on one engine on multiple engine aircraft).

3.4.4 .2.2.6 Afterburner 00 eration. When an afterburner or similarpower augmentation is provided, afterburner 1 ight-off shal 1 bedemonstrated at minimum sustaining airspeeds for successful engine re-light at altitudes from 10,000 feet to the critical operational altitudeof the engine, as defined by the engine specification, in 10,000 footincrements. Flame retention of the afterburner shal 1 be demonstrated tothe maximum engine altitude as installed in the aircraft. Minimumafterburner operation shal 1 be demonstrated from minimum sustainingairspeed to the aircraft engine(s) afterburner combat cei 1 i ng. Minimumafterburner operation at minimum sustaining airspeed shal 1 bedemonstrated at the maximum altitude where this can be demonstrated.

3.4.4 .2.2.7 00 eration with sun. rocket. and mi ssi 1 e firing.Satisfactory engine operation during gun, rocket, and guided missilefi rings shal 1 be demonstrated.

3.4.4 .2.2.8 Anti -icina an d de-icing. Satisfactory operation of theengine ice protection system shall be demonstrated. The capabi 1 ity ofthe engine air induction system to maintain maximum airflow with no iceingestion shal 1 be demonstrated throughout the airspeed/altitudeenvelope.

3.4.4 .2.2.9 Air starts. Three satisfactory air starts on one engineshal 1 be demonstrated at the maximum altitude and minimum speed,corrected for installation, as specified in the engine specification.The maximum altitude at which air starts can be made shal 1 be determined.Air starts shall be demonstrated with manual (emergency) controls, ifprovided.

58


MI L-D-8708 C(AS)

3.4.4.2.2.10 Flame damDing. Satisfactory flame damping shal bedemonstrated in accordance with the test procedure of MIL-O-6728. Al 1phases of flame damping effectiveness shal 1 be reported, with par’ icularemphasis on hazards of night landing approach and takeoffs for bo h landand shipboard operations.

3.4.4.2.2.11 Enciine Performance monitorirm svste m. The functionalcapabi 1 iti es specified in the “Engine Condition Monitoring” requirementof MI L-E-5007 shal 1 be demonstrated. In-flight Engine ConditionMonitoring System (I ECMS) software shal 1 be demonstrated by groundsimulation and during actual flight operations. The level of accuracyand effectiveness of al 1 system maintenance indications, engine component1 ife usage tracking, engine performance degradation trending, and takeoffthrust check indication shal 1 be demonstrated. The IECMS data transferand interface with the required data processing ground station shal 1 bedemonstrated.

3.4.4.2.3 Enciine Dower OUtD ut tests. Engine power output testsshal 1 be performed to determine any power discrepancies and provideaccurate information on pDwer output.

3.4.4 .2.3.1 TurboDroD and turboshaft enaine$ The intermediate-rated equivalent shaft horsepower and maximum pow~r, when applicable,developed by the engine in 1 evel flight at an altitude of approximately5,000 feet and service ceiling shall be determined. This shall notexceed either intermediate rated RPM (maximum continuous if nointermediate rating assigned) or top index temperature (the temperature,turbine inlet or tail pipe, for which the applicable power and RPM is themaximum permissible). The power shal 1 be measured by a torquemeter. Thethrust shal 1 be determined by measurement of change in momentum of theair passing through the engine at the same time. Measurements of TurbineInlet Temperature (TIT) and Tailpipe (TPT) Temperatures shal 1 be verifiedby fuel air ratio combustion temperature calculations. Provision formeasuring turbine inlet temperature wi 11 be furnished by the enginemanufacturer.

3.4.4 .2.3.2 ~. The thrust output developedby turbojet or turbofan engines in level flight shall be determined atfive altitudes within the flight envelope of the aircraft for maximumcontinuous, intermediate, and maximum power settings as specified by theengine manufacturer. The range of altitudes shall include minimum safealtitude, maximum attainable service ceiling for each of the above powersettings, and maximum attainable combat cei 1 ing for each of the abovepower settings. The range of speeds shal 1 include minimum and maximumspeeds attainable in level flight at the combat ceiling altitudes foreach of the above power settings. The thrust shal 1 be obtained bymeasurement of change in momentum of the air passing through the engi ne,or by use of a calibrated thrustmeter.

3.4.4 .2.3.3 R~. The rated thrust output shal 1 bedetermined under conditions (e.g. , temperatures, fuel pressures) on whichpower output is based, in level flight at an altitude of approximately35,000 feet. When direct thrust determination cannot be made, the enginemanufacturer’s “Thrust vs Chamber Pressure” curves shall be used todetermine thrust.

59


MIL-D-8708C(AS)

3.4.4 .2.3.4 Ram-iet and mlse-iet enaines. The rated thrust outputshal 1 be determined under applicable conditions (e. g., temperatures, fuelpressures, altitudes) on which power output is based in level flight.The thrust shall be obtained by the use of a calibrated thrustmeter or analternate method approved by the acqui ring activity for the specificapplication.

3.4.4 .2.3.5 Combination power D1 ants. On aircraft where combinationsof the above engines are installed, the power or thrust shall bedetermined on each type of engine in accordance with the proceduresspecified herein for each type engine.

3.4.4.2.4 Military Dower runs. Mi 1 itary runs shal 1 be performedunder the conditions specified for each type engine. Maximum continuouspower shall be used for military power runs when a military rating is notassigned. High power time limitations shall be established whenapplicable.

3.4.4 .2.4.1 TurbotIroD and turboshaft enaines. A total of one hourof Intermediate power operation in periods of not less than 15 minutesshall be accumulated with the total time eaually divided among thefollowing:

a. Level fl

b. Level fl

ght below 5,000 feet.

ght at cruise ceiling.

c. Climb at airspeed for maximum rate of climb.

Aircraft configuration and data for each of the tests shal 1 be recordedand shall include the following as applicable:

a. Condition of loading.

b. Weight at start of flight.

c. Fuel and oi 1 on board at start of flight.

d. Fuel and oi 1 on board at end of flight.

e. Kind of fuel and oi 1 used.

f. Propeller details, such as design, number of blades, pitchsetting, constant speed, control lable pitch, etc.

9. At five-minute intervals during the run:

1. Standard pressure altitude.

2. RAM (Total ) air temperature at above altitude.

3. Airspeed indicator reading.

4. Engine RPM.

60


MI L-D-8708 C(AS)

5.

6.

7.

8.

9.

10.

11.

12.

13.

14.

15.

16.

17.

18.

19.

20.

21.

22.

23.

24.

25.

26.

27.

28.

29.

Tat 1 pipe total gas temperature.

Oil pressure.

Engine oi 1 inlet and outlet temperatures.

Rear bearing temperature.

Fuel manifold pressure.

Fuel flow.

Air flow.

Tai 1 pipe total pressure.

Compressor inlet total temperature.

Compressor inlet total pressure.

Exhaust nozzle position.

Torquemeter reading.

Temperature of primary structural members subjected totemperatures greater than 200 degrees F.

Main fuel pump inlet pressure.

Main fuel pump discharge pressure.

Emergency fuel pump discharge pressure.

Turbine inlet temperature.

Compressor discharge pressure.

Engine control lever position.

Propeller blade angle.

Input signal to propeller control .

Main reduction gear box oi 1 inlet and outlet temperatures.

Combining gearbox inlet and outlet oi 1 temperatures (ifapplicable).

Time.

Weather conditions.

61

---


I

I

MI L-D-8708 C(AS)

3.4.4 .2.4.2 Turboiet and turbofan enaines. A total of one hour ofintermediate power operation in periods of not less than 15 minutes shallbe accumulated with the total time equally divided among the fol lowing:

a. Level flight below 5,000 feet.

b. Level flight at cruise ceiling.

c. Climb at airspeed for maximum rate of climb.

An additional 15 minutes of continuous operation shal 1 be performed atmaximum cruise ceiling attainable with military power. (This period maybe reduced in duration to maximum allowable continuous operation if thatis less than 15 minutes. ) Aircraft configuration and data for each ofthe tests shall be recorded and shall include the following, asapplicable:


b. Weight at start of flight.

c. Fuel and oi 1 on board at start of flight.

d. Fuel and oi 1 on board at end of flight.

e. Kind of fuel and oil used.

f. At five minute Intervals during the run:

1.

2.

3.

4.

5.

6.

7.

8.

9.

10.

11.

12.

13.

Standard pressure altitude.

Air temperature at the above altitude.

Airspeed indi cater reading.

Engine RPM.

Turbine inlet or turbine outlet total gas temperature.

Oil pressure.

Engine oi 1 inlet and outlet temperatures.

Rear bearing temperature.

Fuel manifold pressure.

Fuel flow. ”

Exhaust nozzle position.

Thrust.

Temperature of primary structural members subjected totemperatures greater than 200 degrees F.

62

L


14.

15.

16.

17.

18.

19.

20.

21.

22.

23.

24.

MI L-D-8708 C(AS)

Air Flow.

Tall pipe total pressure.

Compressor inlet total temperature.

Compressor inlet total pressure.

Main fuel pump inlet pressure.

Main fuel pump discharge pressure.

Emergency fuel pump cfi scharge pressure.

Compressor discharge pressure.

Engine control position.

Time.

Weather conditions.

3.4.4 .2.4.3 Rawlet. mslse-let. and ocket enai nes A total of onehour of operation in periods of not less ~han 5 minutes ”shall beaccumulated, WI th the total operating time divided equal ly among thefollow!ng:

a. Level flight at 45,000 feet.

b. Level flight at service ceillng of basic aircraft.

c. Climb at constant Mach number.

Aircraft configuration and data for each of the tests shal 1 be recordedand shall include the following as applicable:


b. Fuel(s) on board at start of flight.

c. Fuel (s) on board at end

d. Kind of fuel(s) used.

e. At one minute intervals

1. Pressure altitude.

2. Air temperature at

of flight.

during the run:

above altitude.

3. Air speed indicator readings.

4. Fuel pressure(s).

5. Fuel flow.

63


MI L-D-8708C(AS)

6. Engine operating pressures.

7. Thrust.

8. Temperature of primary structural members when temperaturesexceed 200 degrees F.

9. Oxidizer flow.

10. Any other factors concerning the engine which provide abasis for determining satisfactory or unsatisfactoryperformance.

f. Weather conditions.

3.4.4 .2.4.4 Combination of Dower olants On aircraft wherecombinations of the above listed engines are”instal led, all engines shallsatisfy the requirements for that type engine. Unless otherwisespecified, a booster engine shall be demonstrated in level flight at analtitude of 45,000 feet or at the service ceiling (CRT) of the aircraft.The requi red time on booster engine(s) may be accumulated at the altituderequired for the main engine(s) for purposes of combining test programs.

3.4.4.2.5 ProDeller demonstration. The propeller shall bedemonstrated to show compliance with MI L-P-26366 as specified in thedetai 1 specification. This shall consist of operating the propeller atvarious pitch settings and testing for synchronization, synch rophasing,hunting, and surging.

3,4.4 .2.5.1 Low Ditch tests. Low pitch blade stop setting shall bechecked as required by the propel ler manufacturer to demonstrate propersetting and operation. Low pitch stop setting shal 1 be demonstrated tobe compatible with engine operation in all flight phases. Demonstrationsof engine failure modes shall be made after the low pitch stop settinghas been demonstrated.

3.4.4 .2.5.2 Hioh DitCh tests. High pitch (normal) blade stopsetting shal 1 be checked at critical altitude (engine to have torquemeternose). Selected governing RPM shall be maintained for cruising and forful 1 throttle high speed conditions. For tactical aircraft, blade pitchshall be high to prevent excessive engine overspeeding in limit speeddives. On propellers that can “be locked in the normal high pitchposition, a check shall determine if the aircraft can be kept airborne(blades locked in normal high pitch) within the power limitations of theengine. If not, the high pitch stop setting shal 1 be reduced to themaximum at which the aircraft can be kept in the air within safe engineoperating conditions. This test is also applicable to aircraft with anon-feathering propel ler.

3.4.4 .2.5.3 Feathering Ditch tests. Feathering pitch blade stopsettings shal 1 be checked on multi-engine aircraft to determine i ffeathered propel ler windmi 11 i ng occurs on the stopped engine at themaximum 1 evel fl ight speed obtainable with the operating engines.

64


MI L-D-8708 C(AS)

3.4.4 .2.5.4 Reverse Di tch tests. Reverse pitch blade stop(negative) settings shal 1 be checked to determine i f engine rated takeoffRPM will be exceeded at full throttle when blades are against negativestops . For this check the aircraft shal 1 be positioned 90 degrees to thewind. direction.

3.4.4 .2.5.5 Control lever tests. Control , condition, and powerlevers shal 1 be free from automatic S1 ippage under vibration.Sensi tfvi ty of controls shal 1 provide easy and accurate adjustments overthe entire speed or power range. Power changes in relation to powerlever movement shall be essentially linear.

3.4.4 .2.5.6 .sV nchronization and Sv nchroDhasing. The RPM on the slaveengines shal 1 not drop more than 2 percent with the synchronizing or thesynchrophasing system in operation with engines operating at takeoff RPMand with the master engine power lever retarded to flight idle.

3.4.4 .2.5.7 Huntina a nd surainq. Hunting and surging of propellerengine combinations shal 1 not occur for any combination of engine andpropel ler controls.

3.4.4 .2.5.8 Transmission oDeration de monstration. Power plant drivesystems, including any drive shafting, cross shafting and combininggearboxes shal 1 be capable of transmitting ful 1 power from a singleengine and maintaining propel ler synchronization.

3.4.4.2.6 Fuel syste m demons tration.

3.4.4 .2.6.1 Fuel dumDinq. In-flight operation of fuel dumpingarrangements shal 1 be demonstrated in accordance with MI L-F-17874.Fluids other than fuel may be used.

3.4.4 .2.6.2 FU~q . The fuel vent system and impingementtests shal 1 be demonstrated in accordance with MI L-F-17874. Fluids otherthan fuel may be used.

3.4.4 .2.6.3 Enc!ine fuel feed. Tests shal 1 be conducted on theengine fuel feed system(s) to demonstrate compliance with MI L-F-17874 asspecified in the detail specification.

3.4.4 .2.6.4 Fuelina and defuelinq”. Fueling and defueling testsshal 1 be conducted to demonstrate compliance with MI L-F-17874 asspecified in the detail specification.

3.4.4 .2.6.5 Fuel transfe r system. Tests shal 1 be conducted on thefuel transfer system to demonstrate compliance with MI L-F-17874 asspecified in the detail specification.

3.5 Ar ament~n.

3.5.1 Armament Sv stem test. An armament system demonstration testshal 1 be performed to demonstrate that:

a. The firing of guns, launching of rockets or guided missiles, ordropping of stores shal 1 not damage the aircraft structure by

65


I

MI L-D-8708 C(AS)

blast or debris such as links, casings,parachute packs, or diaphragms.

“pig tails,” static lines,

b. Gun gas concentration in the aircraft, during firing, shall notexceed 90 percent of the lower explosive limit (except in theblast tubes and the immediate vicinity of the breech and ventplug). Gun gas measuring equipment shal 1 be approved by theacqui ring activity.

c. All applicable sighting and avionic control equipment shalloperate in accordance with the equipment specificationsthroughout the armament demonstration.

d. At no time during the armament demonstration shal 1 compressorstal 1 or engine flameout occur, nor shal 1 the tai 1 pipetemperature in turbojet and turbofan aircraft rise over theallowable transient over-temperature conditions specified by theengine manufacturer.

3.5.2 Aircraft c on figuration. Except for the instrumentation, theflight test vehicle shall be representative of the production aircraft inall significant respects. The weapons control system shal 1 be configuredto accommodate al 1 the weapons required by the detai 1 specification.14eapons carriage provisions shal 1 accommodate the spectrum of weapons tobe carried. If applicable, the nuclear weapon Airborne Monitor andControl System shall be installed.

3.5.3 Fliaht te St instrumentation. Onboard instrumentation inaccordance with the demonstration instrumentation report shal 1 beprovided. The instrumentation shal 1 be capable of measuring andrecording the fol lowing:

a. Altitude, speed, normal load factor, and attitude during firingor release of weapons and correlating this data with the event intime.

b. Gun gas concentration in the aircraft.

c. Vibration,structure,

d. Mechanicaldefine the

e. Electricalor release

acoustic levels, and dynamic responses of the weapon,and equipment.

interface data between the airframe and the weapon tomaneuvering ,envelope.

impulses from the weapons control system to arm, firea weapon.

f. Photographic or television coverage to record the initialtrajectory of the weapon or store as i t is fired, released orjettisoned from the aircraft. This coverage shal 1 be correlatedwith the above instrumentation.

3.5.4 Contractor demonstration reaui rements. The armamentdemonstration program shal 1 consist of:

66


MI L-D-8708 C(AS)

a. An armament but Id-up program to ensure that a safe and properdemonstration program can be conducted with a safe Interfacebetween the weapons to be carried and the aircraft.

b. A formal ground and flight demonstration in which all of theweapons specified to be carried and launched or released areshown to be compatible with the aircraft and can be employedaccurately within the prescribed maneuvering envelope against asuitable target. Safe jettisoning of those stores which are tobe carried only shal 1 be demonstrated.

3.5.4.1 Armament bui ld-uo Droaram This program shall consist ofboth ground and flight functional test; of the armament system andequipment.

3.5.4 .1.1 Ground functional tests These tests shall include firingof guns, missiles, and rockets as applicable; arming and rearming (thetime required to rearm the aircraft shall be as specified in the detailspecification or the appl i cable portions of MI L-A-8591 , MI L-I-8671 ,andMI L-I-8675); fit testing; release of all droppable stores (normal armingand emergency release); adequacy of safety devices/provisions; adequacy ofhandling equipment; adequacy of installation clearances; evaluation ofarmament hardware/software control i terns; operation of bombing/navigationsystems; adequacy of armament loading tableaus; adequacy of di splay alerts;and adequacy of “stores remaining” tableau. For those aircraft for whichguided missiles are specified, the fol lowing ground tests shal 1 be performed:

a. Aircraft/m~ssile system interfaces.

1. Mechanical. Oefine and verify the physical attachment ofthe missile and launcher to the aircraft. Verify loadcarrying capability of the launchers/pylons, jettisoncapabi 1 ity and other factors pertinent to mechanicalinterface evaluation. The compatibility of all missile loadconfigurations shall be verified.

2. Electrical . Oefine and verify the electrical interface ofthe missile and launcher to the aircraft. Verify theelectrical capability of the aircraft electrical wiringconnecting the mi ssi le to the launcher and the launcher tothe applicable fuselage or wing stations.

3. Controls and di splays. Determine that the location andactuation of controls and di splays are arranged and designedfor timely and coordinated inputs from displays such thatthe aircrew’s interpretation and action to ready and launchweapons or activate electronic and other countermeasures isappropriate, effective and within the al lowable systemresponse time.

b. Weapons control system. Oemasstrate the capabi 1 i ty of theweapons control system to provide correct launch acceptabi 1 ityinputs to the missile for prelaunch, launch, and postlaunchoperation. These tests shal 1 be performed using mixed loads of

67


MI L-D-8708C(AS)

stores and a combination of mi ssi le mode, radar mode andnavigation mode. Error contributions from avionic system,navigation system and control system to mi ssi 1 e performance shal 1be analyzed. Safety of flight demonstrations shall be performedto identify potential incompatibilities between the missi le andaircraft.

3.5.4 .1.2 Environmental factors evaluation. Prior to flight test,an environmental factors evaluation shal 1 be conducted for each weapon orstore to be carried by the aircraft to assess the probabi 1 ity ofenvironmental ly induced damage occurring to either the mi ssi 1 e or theaircraft. Factors to be considered include:

a.

b.

c.

d.

e.

f.

9.

h.

Loads: Maneuver, gust, catapult, landing, ejection (includingejection of other stores).

Dynamics: Vibration, gunfire, aeroacoustic, exhaust (includinglaunch of other stores).

Aeroelastic stability: Flutter, divergence, and aero-servoelastic instability.

Temperature: Flight induced, climatic.

Moisture: Precipitation and spray.

Pressure: Altitude arcing, exhaust plume effects on engineoperation.

Electrical : Power fluctuations, transient EMI, sneak circuits.

Handling: Puncture, abrasion, shocks.

Estimation of the probabi 1 i ty of occurrence of environmentally induceddamage may be based on analyses, reported test results, or documentedservice data. Probability estimates shall be classified as follows:

High: There are definite historical or analytical reasons forexpecting damage.

Medi urn: There is no reason to expect damage except that thestresses will be higher or of a different kind than previouslyexperienced by the weapon.

Low : The weapon has previously survived equal ly severeenvi ronments.

In each instance of high or medium probabi 1 i ty of damage, the specificdamage contemplated shal 1 be defined and classified as to whether itwould affect safety of flight or mission success, or be a logisticburden. Acmrooriate tests to demonstrate that these forms of damaqe wi 11not occur hi to measure their likelihood andpart of the formal armament demonstration.

68

severity shall be pla~ned as


MI L-D-8708 C(AS)

3.5.4.1.3 ~. Functional flight tests shall beperformed to: evaluate armament control i terns within the cockpit; testrelease and control systems; test software envelope/armament 1 imitequations; test software target selection criteria; test software torpedopresetting; fire guns, missiles, and rockets; demonstrate normal andemergency release of applicable stores; and demonstrate the operation ofbombing/navigation systems. F1 ight tests of normal and emergency releaseshould include a suffici ent number of tests to provide a stati stical baseto determine reliabi 1 ity of arming wire systems used to arm fuzes anddeploy stabi 1 izing/retarding devices. For those aircraft for whichguided missiles are specified, the following flight tests shall beperformed prior to launches:

a. Aircraft/mi ssi 1 e system interfaces.

1. Mechanical . In-flight verification of the mechanicalinterface shal 1 be accomplished in conjunction with otherflight tests. The missile shall be captive carriedthroughout the aircraft flight envelope unless 1 imited byinterface loads or the mi ssi le or interface specifications.Instrumentation shal 1 be instal 1 ed to record mechanicalinterface data.

2. Electrical . In-flight verification of the electricalinterface shal 1 be accompli shed in conjunction with otherflight tests. The missile shal 1 be captive carriedthroughout the aircraft flight envelope as specified by theaircraft, missile, or interface specifications.Instrumentation shal 1 be instal led to record electricalinterface data. Successful performance shall be demonstratedfor those conditions and configurations identified for theground functional tests.

3. Controls and displays. In-f] ight operation of armamentcontrols and di splays shal 1 be demonstrated to showcompliance with the aircraft detai 1 specification. Thedemonstration shal 1 include the employment of electronic andoptical countermeasures. The demonstration shall includesimulated mi ssi 1e attack mi ssions wi th combat maneuveraccelerations.

b. Weapons control system. A sufficient number of captive carrylaunch sequences, utilizing instrumented missiles or simulatedmissile load configuration for each type (or major subtype) ofmissile specified, shal 1 be performed to demonstrate thecapabi 1 ity of the weapon control system to provide correct launchacceptability region displays and correct inputs to the missilesfor prelaunch, launch, and post-launch operation. Mixed load

logic and performance in each combination of missile mode, radarmode and navigation mode shal 1’ be demonstrated. A portion of thecaptive carry launches for each type of missile shall bededicated to demonstrating correct inputs to the missile in theelectronic countermeasure environments specified.

69


MI L-D-8708 C(AS)

3.5.4.2 Armament svste m fliaht and around demonstrations Formalf 1 ight and ground denvxstrations shal 1 be performed fol lowing “theanalysis and approval of the data obtained from the bui ldup test program.Prior to performing the demonstrations, the Armament Demonstration TestPlan which shal 1 include the tests and procedures for captive carriage atthe boundaries of the allowable flight envelope, jettison, release, orfiring of all weapons listed in the detail specification shall besubmitted. Carriage and jettl son of external stores which are notnormally released shall be included.

3.5.4 ..2.1 ~. The operation of guninstallation, both fixed and turret mounted, including accessories anddirectly associated equipment, shall be derrcnsstrated. This demonstrationshall include simulated operation, rearming, bores ightlng, groundmaintenance, and operation in-flight. The ground demonstration shal 1include ground firing for dispersion characteristics.

3.5.4 .2.1.1 Heavv attack and Dat rol aircra ft. In-flight operationof the gun installation shall consist of firing two complete loads ofammunition in bursts of not less than 100 rounds from each gun, with allguns firing simultaneously, with three seconds maximum interval betweenbursts. Firing shal 1 be performed under the fol lowing conditions:

a. Altitude: The aircraft shal 1 be flown through the fol lowingaltitude cycle prior to firing:

1. Climb to within 2,000 feet of the design service celling(intermediate thrust) and remain at this altitude not lessthan five minutes.

2. Descend to any altitude under 7,000 feet and remain at thisaltitude not less than five minutes.

3. Climb to within 2,000 feet of design service ceiling(intermediate thrust) and remain at this altitude for notless than 10 minutes and then commence firing.

b. Speed. The first load shall be fired at a minimum stabilizedlevel airspeed. The second load shall be fired during indicatedairspeed within 0.8 Vmax to Vmax.

c. Normal load factor. The first load shall be fired at a loadfactor of 1.0. The second load shal 1 be f I red at a load factorof 0.9nz max or 0.9 maximum safe load factor at the specifiedaltitude.

3.5.4 .2.1.2 Fiahter. trainer and 1 iaht attack a ircraft. In-flightoperation of fixed gun installations shall consist of firing fourcomplete loads of ammunition in bursts of not less than 100 rounds fromeach gun, with all guns firing simultaneously, with three seconds maximuminterval between bursts. Firing of the first two loads shall beperformed under the conditions specified for heavy attack and patrolaircraft. One short duration interrupted burst (interruption of 300 to500 millisecond) shall be conducted. Firing of additional loads, asrequired, shal 1 be conducted under the fol lowing conditions:

70


MI L-D-8708C(AS)

a. Altitude. The aircraft shal 1 be flown through the fol lowingaltitude cycle prior to fi ring:

1.

2.

3.

Climb to within 2,000 feet of the service ceiling (militarypower) and remain at this altitude for 10 minutes and thenfire approximately one-half load. The 10 minute dwel 1 ataltitude may be curtai led as necessary contingent upon theamount of fuel avai lable. (Service ceiling is defined asthat ceiling obtained with the use of afterburner or similarpower augmentation. )

Descend to any altitude under 7,000 feet and remain at thisaltitude not less than five minutes.

Climb to 20,000 feet altitude and remain at this altitudenot less than 15 minutes and then fire the remainder of theload in short intermittent bursts.

b. Speed. The fi ring shal 1 be performed as fol lows:

1. Low speed firing tests. The guns shall be continuously ‘“fi red while the aircraft is maneuvered rapidly fromunaccel erated flight to at least 0.9nzmax and back tounaccel erated flight. The airspeed at the time 0.9nzm x is

?attained shal 1 be within 10 knots above the correspond ngstal 1 speed. The altitude at which the test maneuver isinitiated shal 1 not exceed 7,500 feet. Fol lowing low speedtests at 0.9 nzmax, a firing shall be conducted at O.Og.

2. High speed firing tests. The guns shall be firedcontinuously whi 1 e the aircraft is maneuvered from 1.Ogflight to at least 0.9nzmax and back to 1 .Og flight. Thespeed throughout the maneuver shal 1 be not less than 0.9Vmaxat the altitude at which the tests are conducted. Thealtitudes of the test shall not exceed 7,500 feet.Fo1 lowing the high speed tests, a. fi ring shal 1 be conductedat O.Og.

3. High altitude firing tests. The guns shall be firedcontinuously while the aircraft is maneuvered rapidly to atleast 0.9nzmax at the specified altitude. In addition, allguns shall be fired simultaneously for a duration of fourseconds or a full load whichever is less, at an airspeed nogreater than 1. IVS in cruise configuration (CR) at thespecified altitude. The altitude at which the tests areperformed shal 1 be 3,000 t 1,000 feet below the maximumaltitudes attainable at subsonic speed and at supersonicspeed by the aircraft at combat weight and combat power.

c. Boresight retention. Boresight retention of fixed guns shal 1 bedemonstrated in accordance with MI L-I-8670.

3.5.4 .2.1.3 Gunfire vibration and aeroacousti c environment. Duringground and flight gun firing demonstrations, vibration and a;~a:m:gticmeasurements on the structure and equipment shal 1 be made.

71


MI L-D-8708C(AS)

shall be used to verify and correct predicted design vibration andaeroacoustic levels and dynamic responses of structure and equipment.The data shall also be used with analytical methods to verify that theaircraft and equipment can withstand the gunfire environment.

3.5.4 .2.2 Rocket demonstration requirements. Satisfactory operationof rocket installations shal 1 be demonstrated. This shall includesimulated operation, rearming, bores ighting, ground maintenance, andoperation in-flight. During the rocket firing demonstration, it shall bedemonstrated that the tai 1 pipe temperature in turbojet aircraft does notrise over the allowable transient overtemperature conditions speci fied bythe engine manufacturer,. and that there is no other evidence ofcompressor stal 1 or engine flameout.

3.5.4 .2.2.1 Air-to-wound rockets. In-flight demonstration of air-to-ground rockets shal 1 consist of fi ring two complete loads of inertwarhead rockets of each type specified for the aircraft under thefol lowing conditions:

a.

b.

c.

3.5.

Altitude. The aircraft shal 1 be flown through the fol lowingaltitude cycle prior to fi ring:

1. Climb to within 2,000 feet of the design service ceiling(military power) and remain at this altitude not less thanfive minutes.

2. Descend to any altitude under 7,000 feet and remain at thisaltitude not less than five minutes.

3. Climb to within 2,OOO feet of design service ceiling(mi 1 itary power) and remain at this altitude for not lessthan 15 minutes.

4. Descend to within ground target range and commence firing.

Speed. The first load shall be fired at a minimum stabilizedlevel flight airspeed. The second load shal 1 be fi red duringindicated airspeed within 0.8Vmax to Vmax.

Normal 1oad factor. The first one-half load shall be fired at0.5g and the second one-half load at 1 .Og. The second load shal 1be fi red at 0.9nzmax or 0.9 maximum safe load factor at thespecified altitude.

4.2.3 Guided missile demonstration reoui rements. Satisfactoryoperation of the guided missile installations specified in the detailspecifi cation shal 1 be demonstrated. The demonstration shall consist ofcaptive carry, free flight launches, and jetti son.

3.5.4 .2.3.1 Cagtive carry tests. A series of captive carry flightsshal 1 be conducted in accordance with the Armament Demonstration TestPlan to demonstrate the missile’s ability to withstand the conditionsimposed on i t during operations throughout the aircraft flight envelope.It shall be demonstrated that the missile passes all tests required bythe aircraft/missile interface specification. Following each

72

.


MI L-D-8708C(AS)

demonstration flight, the missile and the aircraft shall be tested In thesame manner as the pre-fl ight test.

3.5.4 .2.3.2 Free fliqht missile launc@. Two loads of missilesshall be launched wlthln the design launch envelope of the mlssl le. Thefirst load shall be fired at minimum stabilized level flight airspeed.The second load shall be fired at the maximum airspeed of theaircraft/missile combination. One missile shall be launched at lowaltitude and at maximum airspeed from the station closest to the aircraftcenterline and farthest aft. The launch shal 1 demonstrate the ability ofthe missile to survive launch and acquire a target. Guidance functions,acceleration, vibration, and control surface motions shall be measuredduring this launch. Electrical power delivered to the missile shall berecorded and any startup transients identified.

3.5.4 .2.3.3 Jettison reau irements It shal 1 be demonstrated thatmissiles can be $etti soned from any of “the carriage stations and that theentire load of missiles can be jettisoned without damage to’ the aircraft.

3.5.4 .2.3.4 Missile v bration and aeroacoustic environmentimeasure ent ests The vibration and aeroacoustic environment induced onthe mis!ile(s) shall be measured for the conditions specified in MIL-A-8870. For each type of missile, an environment measurement vehicle shallbe carried on the station (if carried on more than one) where theaerodynamic turbulence wi 11 be most severe.

3.5.4.2.4 DroDrJable stores.

3.5.4 .2.4.1 ~. Satisfactory operation ofapplicable conventional store installations and associated releaseequipment shal 1 be demonstrated. Conventional stores include bombs,mines, torpedoes, flares, float-lights, sonobuoys, searchlights, fueltanks, etc. This demonstration shall include:

a. Loading and unloading within the time specified in thedetail specification.

b. Maintenance procedures.

c. Check of the control and monitor circuits on the ground and i nflight for all delivery modes.

d. Release of stores in flight. A build-up in airspeed shall beperformed where no previous data (wind tunnel, analysis, etc)exists for any store.

3.5.4 .2.4.1.1 Release of stores in fliaht. Flight demonstrationshall consist of dropping one complete load of stores as fol lows:

a. Type of stores. External stores selected from those required inthe detail specification shall be dropped from the most criticalstations in the most critical configurations, including “mixed”loadings, for each demonstration of release tactics and bombcontrol equipment. Only inert stores shall be used.

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MI L-D-8708 C(AS)

b. Separation. Positive separation shal 1 be demonstrated to occurimmediately upon actuation of the release system with nointerference between the released store(s) and any part of theaircraft and adjacent stores, and with no damage to the releasedstore or to the aircraft. The attitude of store(s) duringseparation shal 1 be such that each store can perform its intendedfunction and shal 1 not hinder the pi lot i n the performance ofappropriate escaPe maneuvers for the type of delivery performed.

c. Release control . Both primary and emergency method of releaseshall be demonstrated.

d. Structural integrity. No evidence of deterioration, damage tothe aircraft structure, adjacent stores or the store itself shal 1occur within the specified flight conditions.

e. Rel ease parameters.

1. Speed. Rel ease of stores shal 1 be demonstrated at theapplicable maximum permissible speed for the aircraft, orfor the store, (whichever is less). The maximum releasespeed shal 1 be recorded.

2. Altitude. For stores capable of being dropped from highaltitudes, release shall be accomplished at 2,000 feet belowthe service cei 1 ing after remaining at this altl tude for 30minutes. For other droppabl e stores (torpedoes, mines,flares, etc. ) the release shall be made at an appropriatealtitude below 3,000 feet.

3. Normal acceleration. The heaviest store load shall bedropped at 0.9nzmax to nzmax or maximum accelerationpermissible for the store. It shal 1 be demonstrated thatal 1 store types can be dropped at 0.5g or at the minimumsafe g established during the buildup flight tests.

4. Dive angle: Stores shal 1 be dropped in the maximum safedive angle established during the buildup flight tests.

5. Release interval . For stores which are released in multiplerelease modes, the full load shall be released at theminimum allowable interval at the most critical combinationof rel ease parameters defined by analyses approved by theTest Authorl ty.

6. Combinations of release parameters. Stores shal 1 be droppedin the most critical combination of subparagraphs 1through 5 above. Unless analyses indicate otherwise, thisshall be maximum airspeed, minimum normal acceleration,maximum dive angle, minimum release interval , and minimumsafe release altitude.

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MI L-D-8708 C(AS)

f. Release tactics. A tactical rel ease shal 1 be demonstrated foreach of the aircraft delivery modes. The tactics to be used forrelease of the various types of stores shal 1 be in conformancewith the mission and bomb control equipment of the aircraft.When specific tactics are not applicable, sufficient releasesshal 1 be demonstrated under varied conditions to define anenvelope of release conditions. The demonstration shall includestore separations at the most critical Mach number and loadfactor combination of the specified flight envelope of theaircraft-store combination. The fol lowing shal 1 be recorded (viatelemetry) at the time of release: airspeed, altitude, attitudein pitch, yaw rate, rol 1 rate, vertical accel eration,longitudinal acceleration, and lateral acceleration.

9. Aircraft guidance and store rel ease system. Satl sfactoryoperation of the aircraft guidance and store release system shal 1be demonstrated. The accuracy of the store drop shal 1 be withinthe limits specified in the detail specification.

h. Jettisoning. Jettisoning of all specified stores shall bedemonstrated. For stores of variable weight (rocket pods,chemical dispensers, etc.), the lightest configuration shall bedemonstrated, unless analyses shows another combination ofweight, e.g. , and Moment of Inertia (MI) to be more critical .For jettisoning tests of external auxi 1 Iary fuel tanks, the tanksshall be jettisoned in the full , half full, and empty conditionsbetween and EAS equal to 1.2V$ at sea level and an EAS equal to0.9VH at sea level , The partially full condition shall be acondition that causes the most critical separationcharacter sties with regard to possible damage to the aircraft orany retained stores. The tanks shal 1 not hang up on the aircraft,and neither the al rcraft nor retained stores shal 1 be damaged.The tanks shal 1 be jettl soned with the aircraft in level flightin the basic configuration. Liquids other than fuel may be usedin the fuel tanks.

3.5.4 .2.5 Nuclear weaDons reaui rements. Operation of nuclear-storeinstallations, including missiles with nuclear warheads, and theassociated suspension and rel ease equipment shal 1 be demonstrated. Thisdemonstration shal 1 include tests of the airborne monitor and controlsystem.

3.5.4.2.6 Arm m nt~. Satisfactory operation of thearmament control installations shall be demonstrated in accordance withMIL-STD-1760. The demonstration shal 1 include servicing and removalexerci ses, bores ighting, simulated ground operational checks, andairborne operation of the armament controls.

3.5.4.2.7 Accuracy. Accuracy of the weapons control system shal 1 bedemonstrated by expending specified ordnance at a sui table target or byuse of release-point-in-space technique.

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MI L-D-8708 C(AS)

3.5.4.2.8 Armament ground SUDDOrt eaui Dment. Armament groundsupport equipment shal 1 be demonstrated to ensure that no equipmentinterference or functional problems exist. Validation of relatedchecklists and technical publications shall be included in thedemonstrations. Ground support equipment shall include missiletransporters, support adapters. missile containers, loaders, and hoi stswith associated adapters.

3.5.4.2.9 Miscellaneous. Operation of miscellaneous armamentinstallations shal 1 be demonstrated to show compliance with the detai 1specification. There shal 1 be no deleterious effects from the operationof these items, such as corrosion resulting from smoke or blast, ordamage from ejected debris. Examples of these items are: armor, smokescreen equipment, target towing gear, chemical dispersal gear, andmagnetic anomaly detection gear. Installation and removal of specialfield conversion kits shal 1 be demonstrated as applicable.

3.6 Carrier suitability demonstration.

3.6.1 Carrier suitability tests. The carrier sui tabi 1 i ty requirementsof the detai 1 specification shal 1 be demonstrated. Tests shall be conductedashore prior to shipboard tests by Navy pilots. Strength of the airframe,control labi 1 ity, engine tolerance to steam ingestion, and optimization ofthe Approach Power Compensator System (APCS)/Automati c Carrier LandingSystem (ACLS) shal 1 be demonstrated.

3.6.2 Aircraft co nfiauration. The aircraft used for the structuraldemonstration of carrier suitability shal 1 have production representativeairframe, engine, and control system. The aircraft used for theAPCS/ACLS demonstration shal 1 be a ful l-system aircraft representative ofthe production aircraft in all significant respects.

3.6.2.1 Center-of-qravi tv Dositions. The center-of-gravitypositions for the tests shall be those which are critical for theindividual test.

3,6.2.2 (iross weight and loadina conditions. For catapult launchesand arrestments, the gross weight and loading configurations shal 1 be asfol lows:

a. Catapult launches shall be made in each of the followingconfigurations:

1. 14ithout bombs, rockets, guided missiles, mines, ammunition,external fuel, or other disposable load items, but with fullinternal fuel.

2. Maximum fuel (same as above, plus the maximum fuel carriedin internal and external stores).

3. Maximum fuel with stores (maximum fuel plus ammunition,bombs, rockets, guided mi ssi 1 es, mines, torpedoes and otherstores). Critical store configurations shall bedemonstrated.

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MI L-D-8708C(AS)

4. Maximum design gross weight with normal landing gearservicing and alternately with the most critical servicingwithin the limits of MI L-A-8863.

5. Partial fuel (fuel loadings selected to cover other grossweights, with and without stores).

6. All other critical store loading configurations

7. Maximum asymmetric store loading.

b. Arrested landings shal 1 be made in each of the followingconfigurations:

1. Clean configuration.

2. The aircraft loaded to attain the weight specified in thecarrier landing design gross weight definition in MI L-A-8860, incrltlcal combination with external stores for which strength forarrested landings is required, and alternate criticalcombinations of lower gross weights and loading configurations.The weight distribution, including ballast, shall be distributedto attain the specified aircraft gross weights. For at least oneof the loadings herein, the landing gear servicing shall be themost critical within the limits determined from the landing gearservicing test of MI L-A-8867.

3. Maximum asynnnetric store loading.

3.6.3 ~. Aircraft to be used for thestructural demonstration of carrier suitabi 1 ity shal 1 be instrumented inaccordance with paragraph 3.2.3.2. For the APCS/ACLS tests, the aircraftshal 1 be instrumented to provide a record of deviations from theprogrammed fl lght path and an airspeed and attitude presentationthroughout the approach.

3.6.4 Facilities fo carrie suitability tests The Government wi 11furnish the facilities r~quired ~or the carrier suitability demonstrationspecified herein and for the buildup tests, and will retain full controlof the facilities during these tests. ,.

3.6.5 Demonstration tf2St reauirellen.k.

3.6.5.1 Demonstration. The carrier suitability demonstration shall beperformed as specified in Table V. Design catapult and arresting hookloads and design load factors shal 1 be attained when applicable. Whendesign load factors are demonstrated, the aircraft gross weight may bereduced as required to avoid exceeding the design 1 lmit catapult orarresting hook loads. Where both 1 imit load and 1 imlt load factor cannot be attained in any one test condition because of the capacity of thefacilities furnished by the Government, the specified gross weight may bereduced by the acquiring activity to attain limit load factor. Criticalconditions shal 1 be approached gradually in buildup tests. The number ofbuild-up tests shall be included in the Carrier Suitability Test Plan andSchedule.

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MI L-D-8708C(AS)

3.6.5 .,2 Con flqurat{on chanqes. After each catapult launch or f!eldtake-off fol lowing an arrested landing, the landing gear and al 1 otherdevices requi red to transl tion from the take-off con f~guration to theclean/cruise configuration and back to the landing configuration shall becyc 1ed.

3.6.5.3 Catapulting. Catapult launches shal 1 be performed todemonstrate that the aircraft can be suitably launched from the catapultsof the aircraft carriers from which it Is required to operate. Absenceof perceptible shimmying and hunting characteristics of the nose gearshall be demonstrated.

3.6.5.3.1 CataDul t accessori~. It shal 1 be demonstrated thatcatapult accessories have the required strength, a satisfactory service11 fe, and are carrier suitable as requl red by MIL-L-22589. MI L-B-851 10,and MI L-A-8863. There shal 1 be adequate clearances between the aircraft,\ ts stores, and ‘the holdback at the time of release of the aircraft fromthe catapult. lt shal 1 be demonstrated that the launch-bar system hassatisfactory extension, holddown, and retraction characteristics; doesnot cause damage, to the catapul t or aircraft components; does notinterfere WI th the cross-deck pendants during arrestments; and does notimpact the flight deck immediately after disengagement from the catapultshuttle spreader at the end of the power stroke. Control of the launchbar to the “up” position shal 1 be demonstrated to be independent from theaircraft engine throttle.

3.6.5.3.2 CataDult SDOttinq (D rior to tensioning. Spottingincluding catapult hookup, suspend. and abort operations aboard aircraftcarriers shal 1 be demonstrated. Both on-center and off-center approachesshall be demonstrated. For demonstrations. the main oear off-centerlocation at the time of holdback release shal 1 be 24 inches from eitherside of the centerline of the catapult or that resulting from a maximum15 degree entry angle (between the center 1 ine of the aircraft and thecenterline of the catapult), whichever is less. This requirement isspecified in MI L-L-22589 and is diagramed in Figure 1. On-center andoff-center launches shal 1 be demonstrated for al I representative grossweights.

LEGEND:

on-center Approach

otl-Center Approach

Entry Into,’Y” Sectlo” &

‘Giu2+&&- —+ ---J-/ 4

‘ --+ .~ ygc:’”;~hCatapult Shuttle

In Tension 4’ ‘>

FIGURE 1. On-center and off-center sDottinq for nose qe ar launch aircraft.

78

L


MI L-D-8708 C(AS)

3.6.5 .3.2.1 Conflauratlo n for cata milting.center spotting conditions shal 1 be demonstrated

Both, on-center and off-for each configuration

of 3.6.2 ”.2a. For the asymmetric configuration, catapult takeoffs shal 1be demonstrated for off-center spotting \n both directions, left andright.

3.6.5.3.3 Co troll abillty Catapult launches shal 1 be performed atthe tnlntmum safe !aunchfng air~peed and with e!ther 40 knots above theminimum safe airspeed, or at the maximum airspeed attainable if the 40knot margin cannot be achieved. Trim is optional , but shall remain fixedduring each launch until an airspeed is reached at which high liftdevices may safely be retracted or turned off (25 knots above the trimspeed for catapult end airspeed when no high lift devices are employed).Under these conditions i t shal 1 be denmstrated that:

a.

b.

c.

d.

There is adequate longitudinal control effectiveness to preventpitch up or pitch down to undesirable attitudes.

The longitudinal control forces are within 20 pounds pull and 10pounds push.

Predetermined control programming or unusual control manipulationby the pilot is not required.

Directional oscillations under all combinations of csross weiaht.catapult accelerations, and required spotting conditions are”convergent.

3.6.5.3.4 Aircraft fl iaht contro 1 svstem. During the catapultlaunching tests, the effectiveness of the airc~aft flight control systemsIn the normal and emergency conditions, (including the switch-over to andfrom the normal and emergency systems) shal 1 be demonstrated.

3.6.5.3.5 Steam inaestion tests. It shal 1 be demonstrated that theengine is not affected or is tolerant of steam ingestion by launches froma shorebased “degraded” catapult that is typ!cal of the “worst case” of aworn shipboard catapult. This demonstration shal 1 be conducted for al 1engine power levels avai lable for a shipboard take-off.

3.6.5 .3.6 Jet blast de lectof aco Ustic thermal en ironment testCatapult aeroacoustic and thermal rtests shal 1 be conductedvashore in “

and

accordance with MI L-A-8870 to demonstrate that the aircraft can withstandthe catapult environment immediately forward and aft of the Jet 81astDeflector (JBD) without adverse effects on the aircraft structure,structural components, or engine operation. The proposed testarrangement shal 1 be provided at the Structural Ground Loads and CarrierSuitability Derrmstration Planning Conference.

3.6.5.4 Arrest ing. Arrested landings shal 1 be performed todemonstrate that the aircraft can consl stently engage the arresting gearand that aircraft motions durl ng the arrested run-out are conducive tosafe shipboard arrestments. It shal 1 be demonstrated that there 1s nocable impact damage to the aircraft or stores during arrested landings orbolters for all landing conditions and landing configurations. Thearresting system shall be suitable for arrested landings in accordance

79


MI L-D-8708 C(AS)

with MI L-A-18717 and MI L-A-8863. Satisfactory swivel ing of the nose gearfor rol 1 back in the arresting gear shal 1 be demonstrated. Satisfactoryanti-hunting and shimmy characteristics of the nose gear shall bedemonstrated. Abrupt application of brakes during the post arrestingrol l.-back shal 1 be demonstrated.

3.6.5.4.1 Arrestina configurations. The tests of Table V shal 1 bedemonstrated for each of the arrested loading configurations of 3.6.2.2b.

For the asymmetric configuration, Test “b” shal 1 be performed off-center

to the left and repeated to the right. The nomenclature and symbol i sm ofTable V are specified in 141 L-A-8863.

3.6.5.4.2 Arres ti na book damoinq. It shall be demonstrated that thearresting hook has satisfactory damping fol lowing impact WI th a deckobstruction. The effect of under serviced arresting hook damper(s) onarresting hook dynamics following impact with a deck obstruction shal 1 bedemonstrated.

3.6.5.4.3 AoDroach sDe eds. A range of approach speeds from VpAminto 15 knots above 1.1 VpAmi n shall be demonstrated.

3.6.5.4.4 Wave-off caoab tyili Wave-off capabi 1 ity under the moststringent approach conditions shal i be demonstrated.

3.6.5.5 Fliqht control svstems.

3.6.5.5.1 Automated Fliqht Control Svstem (AFCS1. The AFCS shal 1 bedemonstrated to show compliance with the requirements of MI L-F-9490 andMI L-C-18244 as specified in the detai 1 specification.

3.6.5.5.2 ADDrOaCh Power Compensator Sv stem (APCS2.

3.6.5 .5.2.1 APCS qround te Sts . Prior to carrier sui tabi 1 itydemonstration, ground demonstrations shal 1 be performed on the approachpower compensator system to show compliance with the requirements ofMI L-C-23866 as specified in the detai 1 specification.”

3.6.5 .5.2.2 APCS fliqht tests. Satisfactory performance of the APCSshal 1 be demonstrated ashore for both manual and automatic carrierlandings.

3.6.5.5.3 Automatic Carrier Landinq Svstem (ACLS1.

3.6.5 .5.3.1 ACLS simulation demonstration. A simulation of the ACLSshal 1 be conducted to verify that the predicted performance meets therequirements of AR-40 (both closed and open loop). The simulation shal 1be updated with any changes made to the aircraft or aircraft data baseand shall be verified with the flight test results. The simulation shallbe repeated when significant updates are requi red.

suitab3.6.5 .5.3.2 ACLS around demonstration. Prior to the carrier

lity demonstration, the following shall be completed:

80


t41L-o-870nc(As)

TABLE V. Arreste d landing te~.

1 2 3 4 5 6

rest Type of Sinking Pitch Roll Remarksno. landing speed (FPS) angle (do.a) angle (dew)

a on Not less Optional Optional Attain limit hook load.center

than Vvc

b off Attain limit hook load, 25 feetcenter off-center.

c Rolled Mean *1 Not lRIS Attain limit hook limlt.than 6

d Rolled Optional Not less Perform twice, once with roll inand yawed than 5 same direction as yaw and once with

roll in opposit~ direction to theyaw. The yaw angle shall not be

0ss an eqrees.

e Tail Not less Not less optional perform once to the conditionsdown than mean specified or, alternatively three

than ~vc +3 times but with sinking speed notless than 0.8 times the specified

+3 u Vvc sinking speed.

f Nose Not greaterdown than mean

9 Hem Hem *1.5 See Note 1

h Free Not more Not less Perform once to the conditionsflight than angle specified or, alternatively threeWi thout than ~vc correspond-deck

times but with the s ecified sink-ing to 1.3W 1.ing speed increased y 2 FPS and

;h:ruc- -3 u Vvc lift at the speci f led Pi tch a.gle reduced1 .05vp~, n by 2 degrees. The hook load forat wire all free fl Ight engagements shallenaa9ement not be less than 85 percent Of

limit.i Free Not 10ss

fl{ght than thewi th angledeck corrospond- See Note 2obstruc - {ng to l.OWti.a” lift ●t

1. 05vp,&i”at wireengagement

81


MI L-D-8708 C(AS)

TABLE V. Arrested landina tests - continued.

to

I 82

b


MI L-D-8708 C(AS)

a. Continuity checks of all system wiring.

b. Measurement of all signal transport delays from end to end(sensor output to control surface command).

c. Veri fi cation of data 1 ink and Instrument Landing System (ILS)displays switch operation, discretes, and data polarity and scaling.

d. Measurement of ACLS, AFCS, and APCS component static gains andresponse to step and sine wave inputs. This may be performed ona 1 aboratory bench.

e. Measurement of the control surface response to sine wavecommands.

f. End to end measurement of the total ACLS airborne system staticgains and hysteresis characteristics (all command and sensorinputs to control surface). If feasible, these measurementsshal 1 be made with the sensors removed from the aircraft andmounted on calibration equipment. Otherwise, the signal “substitution method can be used.

3.6.5 .5.3.3 Automatic Carrier Landina Sv stem (ACLS) functional checkm. A functional check flight shal 1 be performed to verify that theaircraft ACLS instal Iation, including the radar augmenter, data link,cockpit di splays and controls, ILS, AFCS, and APCS are functioning properly.The aircraft shal 1 provide a stable, repeatable response to ACLS commands andshal 1 not inadvertently uncouple when under automatic control.

3.6.5 .5.3.4 ACLS ooen looD fliaht demonstration. Flights todemonstrate at rcraft response to open loop ACLS step and sine wavecommands shal 1 be performed. The aircraft response shall match theresults of the ACLS simulation.

3.6.5 .5.3.5 ACLS closed looD fliaht de monst ration. Flights todemonstrate aircraft response to closed loop ACLS step and sine wavecommands and aircraft performance during normal ACLS Mode 1 approaches.’shal 1 be performed. The aircraft response to step and sine wave commandsshall match the results of the ACLS simulation. The aircraft shal 1provide stable, repeatable responses during Mode 1 approaches and shal 1not inadvertently uncouple.

3.6.5.6 Vertical /Short Take-Off and Landina (s TOL) aircraft.

3.6.5.6.1 co ntrol and Performance character sti cs Take-of f,approach and landing character sties shal 1 be demons tr~ted in VerticalTakeoff (VTO), Vertical Landing (VL), Short Takeoff (STO), Short Landing(SL), and hover (as applicable) at the minimum guaranteed installedengine thrust.

3.6.5 .6.2 Exhaust aas inaestion. Engine tolerance to exhaust gasingestion shal 1 be demonstrated in the VTO/VL for all Dower level s.-

3.7 Installed Sv stems demonstration

83


MI L-D-8708 C(AS)

3.7.1 Installed systems and ea uiDment. Oemonstrations of thesystems and equipment installed in the aircraft shall consist ofground and flight tests as applicable.

3.7.2 Svstems configuration. Instal led systems to be demonstratedshall be representative of those in the production aircraft. Ifcampatibi 1 ity with the basic airframe and engine is to bedemonstrated, they shal 1 be representative of the production aircraft.

3.7.3 Test instrumentation. Where test data is recorded during thedemonstration, instrumentation necessary to show compliance with therequirements of the detail specification shall be installed.

3.7.4 Avionic Sv stem demonstration. It shal 1 be demonstrated thatthe performance, instal lation, and compatibi 1 ity of the avionic systemmeets the requirements of the detai 1 specification in al 1 modes ofoperation.

3.7.4.1 Installation. It shal 1 be demonstrated that theinstallation of all avionic equipment and related accessories of thesystem complies with the requirements of MI L-I-8700 and the applicableequipment installation specification.

3.7.4.1.1 Temperature. Adequate avionics cooling shall bedemonstrated in accordance with MI L-E-18927 under al 1 ground and flightoperational conditions of the aircraft. Ground demonstration shal 1include al 1 ground cooling modes of operation including engines,Auxi 1 iary Power Units (APU), on board fans, external cooling cart,external pneumatic cart, or any combination thereof, if applicable. Theambient temperature in al 1 compartments containing avionics equipment andindividual avionics exhaust temperatures shal 1 be demonstrated to bewithin the values of the individual equipment. specifications or MI L-E-5400,whichever is more stringent. Temperatures measured in accordance withMI L-T-18606 shal 1 be monitored by a thermocouple or similar sensorand records shal 1 be maintained of temperature with simultaneousrecordings of compartment ambients, forced air, or liquid coolanttemperatures, and flow rates at the equipment coolant inlets. Theserecorded data shal 1 be summarized in the Avionics System DemonstrationReport.

3.7.4 .1.2 Condensation. It shal 1 be demonstrated in accordance withMI L-E-18927 that following ground and flight tests, air ducts toequipment are free from moisture after each test. Equipment fai lures,either permanent or temporary in nature, shal 1 be investigated andreported.

3.7.4.1.3 Vibration and shock loads. It shall be demonstrated thateach avionic equipment is not subjected to vibration or shock loadsgreater than the limits of the equipment specification.

3.7.4.1.4 Interface tests. It shall be demonstrated that interfacerequirements for each equipment, e.g. , power, signal , fluidal , andAutomatic Test Equipment (ATE) meet individual equipment requirements.

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MI L-D-8708C(AS)

3.7.4.subsystemsMI L-STO-87demonstrate

.5 Antennas. It shal 1 be demonstrated that antennaas installed In the aircraft, meet the requirements ofand the applicable equipment specifications. Flight

Dns to substantiate model radiation patterns and otherlaboratory results shal 1 be Derformed to verify the capabi 1 i ty of theavionics ~ystem to meet the specified aircraft-missions. It shall bedemonstrated that:

a.

b.

c.

d.

e.

The azimuth and elevation coverage of antennas of the variousaircraft configurations at the required frequencies, are withinspecified values.

The gain of the antennas, with reference to the i SOtrOpi Cradiator, is adequate to accomplish mission requirements.

Isolation between antennas and between systems using a commonantenna is adequate to prevent impairment of the operation ofeither system.

The mechanical operation of rotatable and other antennas havingmoving parts, and antennas with other control lable features,operate satisfactory and coverage is within specified values.

When operated at ful 1 power, the antenna shal 1 not exceed themaximum temperature, input power (RF. control and Power SUPPIY).or aircraft supplied coolant specified in the antennaspecification.

3.7.4.1.6 Ra dar and infrared ea uiDments. It shal 1 be demonstratedthat radar and infrared equipment operate in accordance with applicablespecifications. Al 1 radiation tests shal 1 be conducted at properlyinstrumented faci li ties for control of position and flight path, inaddition to electrical measurements. The demonstration shall include thefollowing:

a. Oetection range and range and azimuth resolution shaI 1 beevaluated during a profi le of typical flight conditions andsystem modes for al 1 antenna patterns. These tests shall beperformed using radar corner reflectors or other known targets.Resolution is defined as the smal lest spacing between a pair ofreflectors which can be discerned on the radar display.

b. Antenna stabilization in pitch, roll, and yaw.

c. F1 ight control and guidance integration.

d. Accessory integration and compatibility.

e. Antenna pattern coverage in the proper polarization field and thecross polarization field.

f. Indicator display in all radar (and IR) modes under all ambientlight levels and flight tactics within the specified performanceenvelope.

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MI L-D-8708 C(AS)

g. Dot f lyabi 1 i ty and snap-up features, If any,

h. Counter-countermeasures procedure and circui try.

3.7.4.1.7 vstem Elect ~A ~C) a dElect

EMromaanetic Interference (EM;). It shal 1 be dermnstrated th~t EMC

and EMI for al 1 avionic subsystems and equipment comply with therequirements of MI L-E-6051 and MI L-STD-461 as specified in the detai 1specification. The i ntrasystem electromagnet-l c performance of al 1aircraft equipment and subsystems shal 1 be demonstrated. Equipmentsshal 1 operate without mutual interference or degradation of performancein accordance with the detai 1 specification.

3.7.4 .1.8 ~stem Elec~tVulnerability

ic Compatibility (Electrom~(EMV)). It shall be demonstrated that all avionic

subsystems and equipment remain mission capable without endangeringsafety of flight or causing mission abort during or after exposure to theexternal electromagnetic environments specified in MI L-HDBK-235-2. Al 1aircraft equipment and subsystems shal 1 be demonstrated to operate whenexposed to shipboard, aircraft, and land-based emitters.

3.7.4.1.9 ~. It shal 1 be demonstrated that sensorsubsystems requiring aircraft external optical apertures meet the detai 1specification requirements for EMI/EMC/EMP including Fleet contaminationsituations and other requirements such as Radar Cross Section (RCS) andInfrared (IR) signature suppression specified in the detail specification.

3.7.4.1.10 Nuclear Electro aqnetic Pulse (NEMP) . It shall bedemonstrated that the aircraft !emains mission capable after exposure tothe NEMP environment in DOD-STD-2169 as specified i n the detai 1specification. Flight critical and mission essential equipments shall beevaluated in simulated NEMP environments to verify and determine theirlevel of NEMP protection.

3.7.4.1.11 Ha ards o f Elect o aa etic Ra diation to Perso el (HERPlIt shal 1 be demonstrated that co~t~olnof radiation levels is !~ff icient “to preclude hazard to personnel. HERP levels, identified to personneloutside the aircraft who are exposed to on-ai rcraft emi tters at variousangles/di stances, shal 1 be demonstrated to meet the requirements of MI L-STD-1385 as specified in the detail specification.

3.7.4.1.12 Ha ards o f Elect o aanetic Radi ation to OrdnanceIt shal 1 be demonstrated that th~ !esign precludes hazards andperformance degradation in the electromagnetic environment specified inthe detail specification.

3.7.4.1.13 Hazards of Elect o aqnet ci Radiat on to FuelI (HERF) Itshal 1 be demonstrated that the d~s!gn precludes the hazards of RF “radiation to fuel as specified in the detail specification.

3.7.4.1.14 Hazards of laser s.. It shal 1 be demonstrated that allaircraft equipment (including sensors) and aircrew can achieve missionessential performance in the presence of laser dazzle or damage energy asspecified in the detail specification.

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MI L-D-8708 C(AS)

3.7.4.1.15 H zard~ Microwaves (HPM>. It shal 1 bedemonstrated that .al 1 aircraft equipment (including sensors) and aircrewcan achieve mission essential performance in the presence of HPMradiation as specified in the detail specification.

3.7.4.1.16 ~1 EMCO It shal 1 be demonstrated that,in the standby mode of operation, no equ~pment emits radiation whichexceeds the EMCON requirements specified in the detai 1 specification.

3.7.4.1.17 Liahtninq. A 1 ightning protection test shal 1 beperformed in accordance with MIL-STO-1795 using the lightning testwaveform of MI L-STD-1 757. Artificial lightning discharge tests shall beperformed with al 1 flight critical subsystems and components instal led.

3.7.4.1.18 ti~q. It shal 1 be demonstrated thatprecipitation static (P-Static) does not adversely affect aircraft safetyor the ability to perform the assigned mission. P-Static control shal 1be demonstrated by instrumented flight into charge conditions or bysimulated ground testing.

3.7.4.1.19 ~. It shal 1 be demonstrated that al 1 securecommunications equipment and associated installations comply with therequirements of the detai 1 specification.

3.7.5 Electrical svstem. Electrical system ground and flight testsshal 1 be performed to demonstrate the capabi 1 i ty of the system to performin accordance with the requirements of the detai 1 specification.

3.7.5.1 ~. It shall be demonstrated thatthe electrical system performs al 1 functfons required by the detaf 1specification. The demonstration shall fnclude accessibility of unftsfor test and adjustment. removal . and handlina for servicfna. It shallbe demonstrated-that the f nstal latfon meets tie requf rement~ of MI L-STD-81O,MI L-W-5088 , MI L-E-7080, MI L-B-8565 , MI L-R-23761 , MI L-E-24021 , MI L-B-81 757,MI L-E-8191O, MI L-B-B3769, 00D-C-85050, MI L-I-B5071 , MI L-E-85583, andOOD-B-85584 as speciff ed in the detaf 1 specf ficatfon.

3.7.5.1.1 ~. It shal 1 be demonstrated thatthe operatf ng temperatures and vibration levels of al 1 electrf c, power,and conversion equf pment are within the speciff cation desfgn 1 fmf tatfonsof the equf pment determined by the equfpment qual f ff cation tests.Additional load banks, as necessary, shall be fnstal led in thedemonstration aircraft for both around and fliaht tests to obtain themaxfmum load on generation and c~nversfon” elec~rfc power equipment.Electrical load equal “to the power needed to support the aircraft or therating of the power producing equf pment, whichever fs greater, shal 1 beaPPl ied to Creneratfon and conversion electric power equfpment for eachoperating condi tfon of the af rcraft. The temperature of one or morecrf tical parts within each equf pment shal 1 be monf tored with simultaneous. . . . . . . . . . -.measurements or compartment amDl ents, Input ano exit temperatures. Flowrates of equf pment coolant shal 1 be determined at the ful 1 rated outputof the equipment, or wf th loads applied to the equipment, whichevertemperature is greater. It shal 1 be demonstrated that the vibration andshock imposed on all equipments are within the specification designlimitations of these equipments determined by equfpment qual f fi cation tests.

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MI L-D-8708C(AS)

3.7.5 .1.2 Prime mover caDacity. It shal 1 be demonstrated that theprime mover del {vers the required mechanical input to the generatingsystem to maintain electrical generating system rated loads and overloads.

.3.7.5 .1.3 Electrical Dower. Aircraft electrical generation andconversion capacity shal 1 be based upon the preliminary load analysis,including excess capacity requirements in accordance with 141L-E-7016.The electrical power to support the aircraft or the rating of the powerproducing equipment, whichever is greater, shal 1 be demonstrated asconforming to the detai 1 specification for each operating condition ofthe aircraft. It shall be demonstrated that the aircraft electric powerconforms to MIL-STD-704 by recording steady state and transient powercharacteristics for voltage (OC and AC), frequency, distortion, DCripple, and frequency modulation at the terminals of at least 10representative separate uti 1 ization equipments under al 1 operattngconditions of the aircraft.

3.7.5 .1.4 Emerciencv electrical Dower. It shall be demonstrated thatthe alternate and emergency power systems deliver power conforming toMIL-STO-704, and their rated capacity meets the requirements of thedetail specification under all operating conditions. This shall bedemonstrated by recording power characteristics at the input terminals of’at least five equipments approved by the Test Authority. Additional loadbanks as necessary shal 1 be instal led in the demonstration aircraft tofully load generation and conversion electric power equipment.

3.7.5.1.5 protection. It shal 1 be demonstrated that the faultprotection system meets installation requirements of MI L-W-5088,MI L-F-5372, MI L-C-5809, MI L-F-15160, and the applicable requirementsof MI L-STO-454 and MI L-E-7080 as specified in the detail specification.

3.7.5.1.6 Liuhtinq. It shall be demonstrated that the interior andexterior 1 ighting systems, cockpit display systems and indicators, andthe integration of internal 1 ighted components comply with MI L-L-18276,MI L-L-85762, and MI L-L-6730 as required by the detai 1 specification.

3.7.5 .1.7 Electrical bondinq. It shal 1 be demonstrated that allelectrical bonding is in accordance with MI L-B-5087 and MIL-STD-1757 withall electrical systems in operation. Measurements shal 1 be performedusing resistance and impedance levels specified by MI L-B-50B7.

3.7.5 .1. B External DOwer protection. It shal 1 be demonstrated thatthe external power protection opens the external power control relaycontrol circuit and isolates the aircraft electrical bus from externalpower when MI L-STO-704 power 1 imi ts are exceeded.

3.7.5 .1.9 8atterv discharqe. It shall be demonstrated that thebattery relay control unit installation meets the requirements of OOD-B-B5584 as specified in the detail specification.

3.7.5.1.10 Fuel nozzle qroundinq. It shall be demonstrated that thefuel nozzle grounding receptacle meets the installation requirements ofMS90298 and MI L-C-B3413 as specified in the detai 1 specification.

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MI L-D-8708C(AS)

3.7.6 Inst rument svstem It shal 1 be demonstrated that the operationof all flight and engine instruments is in accordance with theappli cableinstrument specifications.

3.7.6.1 Pi~8 edi ndi cater) The system shal 1 be demonstrated to show compl Ia[ce withMI L-I-6115”or MI L-P-26292 as specified in the detail specification.

3.7.6.2 Fuel auant i tv Rae systems. The system shall bedemonstrated to show compliance with MI L-G-7940 as specified in thedetail specification.

3.7.6.3 @mDass syste ms. The system shal 1 be demonstrated to showcompliance with MI L-C-7762 as specified in the detail specification.

3.7.6.4denmsstrated

3.7.6.5demonstrated

3.7.6.6

~. The system shall beto show compliance with the detail specification.

kn.~ The system shall beto show c~plianc~ with the detail specification.

Erufne and fli~t instrument tra smitter mount ng~fand vibration mit tests. Groun~ and flight tests shall be

performed to demonstrate that the mounting provisions for the engine andflight instrument transmitters do not exceed the temperature andvibration limits of the transmitter specified in the instrumentspecifications.

3.7.6.7 ~nale of attack s~stems. The system shal 1 be demonstratedto show compliance with the detail specification.

3.7.7 ti~na~eerina demms~.

3.7.7.1 Hu an enaineerlna and cre station demasst atim Theanthropometric !imi ts used for this de~nstration shal lrbe as” specif iedin the detail specification. It shal 1 be demonstrated that:

a. Cockpit cabin arrangements, seat adjustment, plugs, andconnections are compatible with all configurations(summer/winter/special mission) of aircrew flight clothing andman-nmunted flight equipment for all required missions.

b. Cockpit dimensional requirements comply with MI L-STD-1333, andejection clearances are in accordance with MI L-S-18471 asspecified in the detail specification.

c. Design and placement of escape system controls are in accordancewith MI L-S-18471 as specified in the detail specification.

d. Manual egress capabi 1 ity and underwater ejection escapeperformance are In accordance with MI L-S-18471 as specified inthe detail specification.

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MI L-D-8708 C(AS)

e. Aircrew task and workload is reasonable throughout the primaryand secondary missions identified in the detail specification andmeasured by criteria approved by the acquiring activity. Groundsimulation may be utilized if it can be shown to be equivalent tothe flight environment.

f. Aircrew task times and accuracies are within specifiedperformance 1 imits and satisfactory to accomplish the aircraftmission requirements.

9. The demonstration shal 1 include the components and subsystemswhich protect the aircrew (or enhance ml ssion performance) inflight and during threats identified in the detail specification.HYPobaric conditions, thermal extremes, environmental conditions(nuclear, biological, chemical, electromagnetic, vibrating andacoustic), and emergency escape and survival shall bedemonstrated.

3.7.7.2 Cre stat ion and c abin cQndltioning Cockpit and cabinheating, vent{ la;{ng, and defogging systems shal i be demonstrated to showcompliance with MI L-H-18325 as specified in the detail specification withcockpit systems and man-mwnted components in use. The test procedureshall be as specified in MI L-T-18606. The adequacy of cockpit and cabincool ing shal 1 be demonstrated on the ground and in f 1 Ight with theminimum possible heat generating electrical/electronic equipmentoperating. Al 1 tests which demonstrate heating adequacy shal 1 beperformed when ground static ambient temperatures are 20 degrees F orless.

3.7.7 .2.1 Contain nationi Ground and f 1 lght tests shal 1 be performedto determine the concentration of contaminants such as carbon monoxide,fuel vapors, gun and rocket gases, gaseous products of combustion, andoil mists. It shal 1 be demonstrated that the 1 imits for fuel vaporconcentration and other contaminants (which cause a perceptible odor orirritation or interfere with visibility) comply witis MIL-H-18325 andMI L-E-18927 respectively as specified in the detai 1 specification.

3.7.7 .2.2 Pressur zed ai ircraft. Cockpit and cabtn pressurization,atr condi ttoning, and defogging systems shal 1 be demonstrated to showcompliance with the detail specification. The test procedure shal 1 be asspecified in MI L-T-18606.

3.7.7 .2.3 No n-Pressu rizeci atrc raft. Cockpit and cabin heating,venti lating, and defogging systems shal 1 be demonstrated to showcompliance with the detail specification. The test procedure shal 1 be asspecified in MI L-T-18606.

3.7.7 .2.4 tieous a nd liauid oxvcLL n. With the oxygen system,gaseous or liquid, filled to normal capacity, and with full operatingequipment aboard, the aircraft shal 1 be flown at the minimum and maximumoperational altitudes at which oxygen is required. Under simulatedtactical conditions at those altitudes, the oxygen system shall bedemonstrated to function properly in accordance with MI L-D-8683 orMIL-D-19326 as specified in the detail specification, as applicable, and todemonstrate adequate freedom of movement of personnel to perform theirrequired duties.

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MI L-D-8708 C(AS)

3.7.7 .2.5 n-Board x~ BOGS). Undersimulated operational conditions, the OBOGS shal 1 be demonstrated tofunction in accordance with MI L-D-85520 as specified in the detai 1specification. The air supply thermal conditioning shall be demonstratedin flight with static ambient temperature exceeding 90 degrees F. Groundtests to demonstrate the dynamic performance of the OBOGS shal 1 beconducted i n accordance with MI L-D-85520.

3.7.7 .2.6 Thermal protective s Vs tern. The nuclear thermal radiationpi lot or cockpit protective system shal 1 be demonstrated to showsatisfactory operation in accordance with MIL-T-81571 as specified in thedetai 1 specification.

3.7.7 .2.7 A~ level . It shal 1 be demonstrated that theacoustical noise level in occupied spaces does not exceed the valuesspecified in the detai 1 specification. Al 1 sound attenuation devices ormethods shal 1 be employed during the demonstration, Al 1 doors, windows,ramps and canopies shal 1 be closed. Sound measurement procedures usedfor auditory signal transmission and speech intelligibility shall beapproved by the Test Authority.

3.7.7.2.8 Anti-a ISrotective svstem. The anti-g protective systemshal 1 be demonstrated to show satisfactory operation wi thin the flightenvelope.

3.7.7 .2.9 Aviation life SUDOort sw. terns. Demonstrations shal 1 beperformed on al 1 configurations of aviation 1 i fe support systemsincluding interfaces with cockpl t and other aviation life support systemscomponents. The demonstrations shal 1 ensure capabi 1 ity of the integratedsystem to perform each mission 1 ife support function and shal 1 include:

a. The aircrew automated escape system.

b. Normal and emergency operations of aviation 1 i fe support systems.

3.7.7.2.10 ~ a sembly. Adequatestorage provisions in the seats or other accessible spaces for allrequired parachutes, pararafts or other survival kits, and emergencyoxygen equipment shal 1 be demonstrated. Ground and in-flightdemonstrations shal 1 show that storage precludes loss or mi slocation ofequipment, does not interfere with flight operations, and faci 1 i tatesequipment use in emergencies. The demonstration shall include use ofemergency oxygen during flight, whi le carrying out representative missiontasks, and egress during simulated ditching, ejection, and bailoutconditions. If incorporated as part of the escape system, thedemonstration shal 1 be conducted in accordance with MI L-S-18471 .Personnel restraint during arrested landing and adequate and properrelease features shal 1 be demonstrated. Accommodations for al 1 automaticoxygen and parachute actuation devices shal 1 be demonstrated.

3.7.7.2.11 Emeraencv manual eqress svstem. Emergency evacuation forsimulated post crash conditions (ditching and land crash) and evacuationtimes shall be demonstrated to show compliance with MI L-STD-1472.Sequence of emergency escape for ditching shall be demonstrated to showcompliance with the ditching plan. The adequacy and reliability of

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MI L-D-8708 C(AS)

emergency egress markings and 1 ighting systems shal 1 be demonstrated.The simulated post land/crash evacuation demonstration shal 1 be made toshow the accessibility and suitability with which escape exits can belocated and opened from the inside and the outside of the aircraft forboth landing gear up and landing gear down conditions. Al 1 evacuationdemonstrations shal 1 show the accessibility and adequacy of the emergencyescape openings for escaping personnel wearing. the fl ight gear requi redfor the specified missions of the aircraft.

3.7.7.2.12 Automatic life raft release Svs tern. Operation of theautomatic 1 ife raft release system shal 1 be demonstrated on the ground toshow compliance with the detai 1 specification.

3.7.8 MiSC ellaneous installed systems. A miscellaneous installedsystems demonstration shal 1 be performed for those systems 1 i steal hereinwhich are included in the detai 1 specification. It shal 1 be demonstratedthat each miscellaneous instal 1 ed system is not subjected to vibration orshock loads greater than the 1 imits in the respective systemspecification.

3.7.8.1 Imaciino svstem demonstration. The passive imaging equipmentrequi red by the detai 1 specification shal 1 be demonstrated both on theground and in-flight.

3.7.8.1.1 Ground check. All passive imagery sensors, magazines,recorders, and associated equipment shal 1 be demonstrated to show:

a.

b.

c.

d.

e.

f.

9.

Adequate installation clearances including access for loading andunloading instal led imagery sensors, magazines and recorders;testing, operation, and removal of units and components ofi magi ng equipment.

Ability to rotate sensors and mounts, i f specified.

Functional operation of sensors, sensor control systems,viewfinders and other installations, systems, and equipmentassociated with imaging.

Operational suitability of flight line and bench-checkequipment, if specified.

Proper and safe operation of sensor doors and windows, relatedbay doors, and illuminant release system, if applicable.

Adequate stowage and security of spare imaging equipment, i fapplicable.

Sui tabi 1 ity of handling equipment, if applicable.

3.7.8 .1.2 Fliaht check. A flight test shal 1 be conducted todemonstrate:

a. Sensor platform suitability.

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MI L-D-8708 C(AS)

b. Operation of the sensor control system, throughout the designedrange of the sensor control system but within the design flightenvelope of the aircraft and for the sensors being installed.

c. Suitability and operability of the viewfinder, oblique sights,and other sighting equipment for properly positioning imagingtargets.

d. Adequacy of sensor doors and windows to afford the sensor a viewthat is unobstructed by the airframe, dirt, oil film, watercondensation, reflection or other deleterious effects.

e. Suitabi 1 ity of sensor compartment temperature, pressurization andvacuum supply; accessibi 11 ty to and operabi 1 i ty of doors,windows, sensor, and associated equipment as appl i cable.

f. Usability of the images from all installed sensors operated inaccordance with b. above, including radar recording and nightimaging, as applicable.

9. Adequacy of the initiating, operating, and indicator mechanismsof the sensor control systems.

h. Adequacy of recording equipment, as applicable.

i. Suitability of the automatic pilot to maintain imaging flightline requirements, as applicable.

3.7.8.2 Air-to-air refuel ina svstem. The capability and suitabilityof donor and receiver provisions of ai r-to-air refueling systemsspecified in the detai 1 specification shal 1 be demonstrated in accordanceWith MI L-A-19736. Aircrew visual access requirements specified in thedetai 1 specification shal 1 be demonstrated. The fol lowing features ofair-to-air refuel ing tanker equipment shall be demonstrated when tankercapabilities are required by the detail specification:

a. Hose and drogue stabi 1 ity.

b. Reel Response.

c. Effects of the tanker wake and external stores on the drogue andthe receiver aircraft.

d. Engagement envelope.

e. Static electricity and other environmental effects are not of adegrading nature.

3.7.8.3 Fire warnino. bleed air leak detection and fireextinaui shina s vstems and fire/exDlosion suoDression s vstems. Ground andflight operation of the fire warning system shal 1 be demonstrated to showcompliance with MI L-F-23447 as specified in the detai 1 specifi cation.Extinguishing agent concentration level shall be measured in flight.

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MI L-D-8708 C(AS)

3.7.8.4 ~. Operation of all hydraulicand pneumatic system installations (in flight and on the ground asapplicable) and the accessibility and suitability of external hydraulicand pneumatic power connections shal 1 be demonstrated in accordance ‘withMI L-T-5522.

3.7.8.5 Ice orgte ction svstems. It shal 1 be demonstrated that theice protection system (antf-ice and de-ice) operates satisfactorily inthe icing conditions specified in the detail specification. The icingsurvey test shall include the following:

a. Increase in power required as a function of ice accretion.

b. Capabi 1 ity of the engine air induction system to maintain maximumair flow and ensure against ice ingestion.

c. Capability of the windshield to maintain visibility requirements.

d. Aircraft controllability.

e. Heat transfer performance of the anti-ice and de-ice systems.

f. Assessment of structural damage due to ice shedding.

9. Vibration 1 evels during de-ice system cycling.

h. Proper operation of al 1 ice protection system equipment andcontrols.

3.7.8.5.1 Thermal anti-ice SY te s These systems shal 1 bedemonstrated to show compliance wi ~h {1~-T-18607 as specified in thedetai 1 specification.

3.7.8 .5.2 Pneumatic anti-ice systems. These systems shal 1 bedemonstrated to show compliance with MI L-S-8512 as specified i n thedetail specification.

3.7.8.5.3 Fluid anti-ice systems. These systems shall bedemonstrated to show compliance with the detai 1 specification.

3.7.8.6 Rain removal svstems. These systems shal 1 be demonstratedto show compliance with the detai 1 specification and MI L-T-5842. Theconditions for demonstration shall be as specified in the detailspecification.

3.7.8.7 Watertic!htness. Watertightness (including al 1 systems)shal 1 be demonstrated both on the ground and in flight to show compliancewith MI L-W-6729 as specified in the detail specification.

3.7.8.8 Airframe movable components and sub-svstems. Operation ofall movable airframe components (e.g. ,flaps, enclosures, wing folding,slats, speed reduction devices, and landing gear) shall be demonstratedat the design limits required for such items. The time requi red foroperation shal 1 be recorded.

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MI L-D-8708 C(AS)

3.7.8.8.1 Nina foldina or sweeDinq and SD readi na (s hiwbased aircraft).Fold, sweep, or spread of wings shal 1 be demonstrated to show compliance withthe detai 1 specification.

3.7.8.8.2 Landina ~ear.

3.7.8 .8.2.1 Retraction and extension. The following landing gearoperations shal 1 be demonstrated to show compl iance with the detai 1specification:

a. Time for retracting and locking after takeoff.

b. Extension and locking at maximum airspeed.

c. Emergency extension.

d. Proper functioning of the gear warning system.

3.7.8 .8.2.2 Nose a ear steering. The nose gear steering system shal 1be demonstrated to show compliance with the requirements of the detai 1specification.

3.7.8 .8.2.3 Brakes. The ability of the brakes to prevent rotationof the wheels under the conditions of ful 1 mi 1 itary power/maximum thrustand maximum takeoff gross weight, with the aircraft parked on a dryconcrete surface, shal 1 be demonstrated. The abi 1 i ty of the brakes toretard the aircraft to a safe stop after high-speed landings, withouttire and wheel explosion, shal 1 be demonstrated with anti-skid both“ON” and “OFF. ” With anti-skid “ON,” the abi 1 i ty of the brakes to retardthe aircraft to a safe stop after high-speed landings shal 1 bedemonstrated on a concrete runway with each alternate 50 foot length ofrunway thoroughly soaked with water. Runway length shal 1 be compatiblewith mi ssion requi rements. The abi 1 i ty of the brakes to conform to aturn-around time as specified in the detail specification shall bedemonstrated. Power off braking capabi 1 i ty shal 1 be demonstrated forcarrier deck spotting and maneuvering. The emergency brake controlsystem shal 1 be demonstrated.

3~8 Reliability and maintainability demonstration.

3.8.1 Reliability a nd maintainability A Reliability andMaintainabi 1 i ty (R&M) demonstration shal 1 be conducted to show that theaircraft, meets-the reliability, maintainability, and Built-In-Test (BIT)requi rements speci fied in the detai 1 specification. This test may beperformed in combination with or in addition to structural , aerodynamic,propulsion, shipboard trials, installed systems testing, etc. Any R&M testcompleted and properly witnessed by the Test Authority in accordance withthe R&M Demonstration Test Plan, but prior to the scheduled test, shall beincluded in the Demonstration Planning and Progress Reports and may beproposed as ful fi 11 i ng demonstration requirements.

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MI L-D-8708C(AS)

3.8.1.1 ~. A testability demonstrationshal 1 be performed in conjunction with the maintai nabi 1 ity demonstrationrequired in 3.8.1. Testability data collection and analysis planningshal 1 be performed in accordance with Task 103, MI L-STD-2165 and theSupport Equipment (SE) chapter of the Integrated Logistic Support Detai 1Specification (I LSDS). This requirement shall be included in the R&MDemonstration Test Plan.

3.8.2 Aircraft chanaes. After release for reliability andmaintainabi lity test, no changes shal 1 be made without the approval ofthe acquiring activity.

3.8.3 Test fliqhts. The mission profiles :specified in the detailspecification shal 1 be flown during the R&M demonstration. R&M datashal 1 be CO1 lected during pre-fl ight checks, throughout the flight, andduring post-flight ground testing and maintenance and shal 1 be inaccordance with the requirements of the detai 1 specification, OPNAVINST4790.2, MI L-STD-470, MI L-STD-471 , and MI L-STD-785.

3.8.3.1 Maintenance. In-flight equipment maintenance shall beperformed only when necessary to restore the aircraft to a minimumacceptable condition for crew safety or as permitted by approved Navyoperator maintenance procedures. Al 1 maintenance performed between R&Mflights shal 1 be accompli shed by a maintenance crew whose compositionshall be limited to the number and qualifications equivalent to thosespecified for Navy personnel. Al 1 support equipment to be used duringthe R&M 81T test shal 1 be that planned and specified for use with theaircraft in its service environment.

3.8.4 R&M data and review. Organizational level reliability,maintainability, and bui it-in test parameters on al 1 aircraft equipmentrequi red to meet the specification R&M requirements shal 1 be monitoredduring the entire flight test program. A joint contractor and Navy R&Mreview board shall determine the relevancy of the data used in evaluatingcompliance to specification R&M requirements in accordance with Navyapproved procedures.

3.8.5 SUCIDOrt demonstration. Compatibi 1 ity between the aircraftand its systems and al 1 recommended and specified support equipmentshal 1 be demonstrated. A performance, operabi 1 i ty, rel iabi 1 i ty,maintainability, and testability demonstration shall be performed for allpeculiar support equipment. Al 1 support equipment requi red fororganizational and intermediate maintenance 1 evels shal 1 be demonstrated,and al 1 organizational 1 evel support equipment and systems shal 1 be ofproduction configuration suitable for Fleet use.

3.8.5.1 Scmortabi 1 i ty demonstration. Demonstration ofsupportability characteristics shall be in accordance with thesupportability assessment plan developed as an output of Task 501 ofMI L-STD-1388-1 .

3.8.6 Accessorv equi Dment All accessory equipment shall bedemonstrated to show compliance with the detail specification.

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MI L-D-8708 C(AS)

3.8.6.1 Winches and hoists. Winches and hoi sts shal 1 be operatedthrough at least six cycles at their maximum rated capacity. Operationof remote controls shal 1 be demonstrated.

3.8.6.2 Carao carrvina and handl inq. Al 1 cargo carrying, handling,and securing equipment shal 1 be demonstrated to their rated capacities.

3.8.6.3 Tie-down. Iackina. and t owi nq. Ti e-down, jacking and towl ngprovisions shal 1 be demonstrated.

3.8.6.4 Hoistinq slinq. Operation of the hoisting sling shall bedemonstrated.

3.9 Svstem sa fetv demonstration. The contractor shal 1 demonstratecompl lance with the safety requirements of MI L-STD-882 for criticalhardware, software, and procedures. Where hazards are identified and i tcannot be determined by analysis or inspection whether the correctiveaction wi 11 adequately reduce the risk, safety tests shal 1 be conductedto evaluate the effectiveness of the corrective actions. The analysis ordemonstration tests shal 1 include verification of the safety or warningdevices. Induced or simulated failures shall be considered todemonstrate the fai lure mode and acceptabi 1 ity of safety criticalequipment and software. These tests shal 1 be performed in combinationwith or, if necessary, in addition to other demonstration tests.

3.10 Sv stem survivabi litv/vulnerabi 1 itv demonst ration. Thesurvlvabi llty demonstration shal 1 include evaluation of characteristicsand performance requirements as specified in the detal 1 specification.The survivability demonstration shal 1 include measurement of the system’ssusceptibi Iity to being detected, tracked, and hit by enemy weaponsystems because of each of Its specific observable, e.g. , radarsignature, IR signature, acoustic signature, intentional andunintentional emissions, visibility, or other observable specified inthe detai 1 specification.

3.10.1 Susce otibilitv de monstration. The ability of the aircraft toavoid being detected, tracked, or hit by enemy weapon systems, asrequi red by the detai 1 specification, shal 1 be demonstrated.

3.10.1.1 l?ada r siqnature measurement. Radar Cross Section (RCS)shal 1 be measured to demonstrate compliance with the detai 1 specificationrequi rements.

3.10.1.2 Infrared radiation. Infrared measurement of the aircraftin-flight shal 1 be conducted to demonstrate compliance with the detai 1specification requirements. The contractor shal 1 arrange with thecognizant infrared measurement faci 1 ity/activity in sufficient time topermit scheduling of aircraft and ground facilities equipped for IRmeasurement. The infrared measurement shal 1 be made during a dedicatedperiod; no other tests shal 1 be conducted concurrently.

3.10.1.3 Acoustic sianature. Acoustic signature shall be measuredto demonstrate compliance with the detail specification requirements.

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MI L-D-8708 C(AS)

3.10.1.4 Intentional and unintentional emissions. System emissionsboth intentional and unintentional from electrical , electromagnet c orother components shal 1 be measured to demonstrate compl iance with thedetai 1 specification requirements.

3.10.1.5 Visible. UV. and other short wavelength Dhenomena.Detectability by emission or reflection of energy in wavelengths of 0.7micrometers and shorter, as requi red by the detai 1 specification, shal 1be demonstrated.

3.10.1.6 Countermeasures demonstration. The effectiveness ofelectronic or other device requi red by the detai 1 specification thatreduces or deters the enemy’s abi li ty to inflict an attrition or missionki 11 upon the system shal 1 be demonstrated.

3.10.2 vu lnerabi li tv reduction demonstration. The combat/operationalsuitability of the aircraft in terms of its ability to withstand theanticipated mission threat environment specified in the detai 1 specificationshal 1 be demonstrated.

3.10.2.1 Ballistic and warhead tolerance demonstration. The abilityof the system to withstand the projecti les, fragments, and warheadsspecified in the detai 1 specification shal 1 be demonstrated by 1 ive firetests.

3.10 .2.2 Nuclear hardness and hardness assurance demonstration.Hardness to nuclear effects such as blast, gust, thermal , ElectromagneticPulse (EMP), or initial ionizing radiation (Transient Radiation Effectsto Electronics (TREE), etc. ) required by the detail specification shallbe demonstrated. Hardness assurance shal 1 be demonstrated.

3.10.2.3 Se cial vulnerability ea uiDment demonstrations. Specialequipment requi red by the detai 1 specification to reduce or preventthreat .effects on the system such as fire and explosion suppressionsystems, directed energy weapon protective devices, NBC fi lters, armoredor special clothing, etc. shall be demonstrated.

3.10.2.4 Nuclear. Biological and Chemical (NBC) warfare suitabilityde monstration. The ability of the system to perform its missionessential functions under NBC warfare conditions requi red by the detai 1specification shal 1 be demonstrated. This shall include intrusion tests,over pressure system/ECS filter system test, operabi lity/maintainabi 1 ityin NBC protective ensembl es, and decontamination.

3.10.2.5 Hardness to directed enerav and other soec i fi ed weaoonsdemonstration. Hardness, as specified in the detail specification, todirected energy and other weapons shal 1 be demonstrated.

3.11 Reoorts.

3.11.1 Format and c!eneral requirements. Reports requi red by thisspecifi cation shal 1 conform with the format and general requirements ofANSI 239.18 and the fol lowing:

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MI L-D-8708C(AS)

a.

b.

c.

d.

e.

f.

il.

Reports of test results shall describe how and to what extent thetests were observed by representatives of the cognizant TestAuthority.

Revl sed material shall bear the same page numbers as the pagesthat are to be replaced, plus the word “revised” and the date ofthe revision. The revised subject matter shall be identlfted.Added pages shal 1 bear the same number as the preceding page,followed by a lower case letter unless the additional pagesfol low the last page of the report.

Symbols, abbreviations, and units, if they do not appear instandard 1 i sts of aircraft nomenclature, or in documents 1 is tedherein pertaining to the material in the report, shal 1 be def lnedin a separate tab Ie of definitions.

Reports shal 1 be bound in a manner that wi 11 facl 1 i tate removal,addition, or replacement of pages without the use of specialdevices.

Reports of more than 10 pages shal 1 be indexed.

Contents of the Demonstration Report shal 1 be sectionalized sodata concerning each principal category, e.g. , aerodynamics,structures, propulsion, armament, carrier suitability, etc. , arepresented on consecutive pages that may be separated from thedata concerning other categories. This does not apply to theindex.

The high AOA/Spin Demonstration Schedule Reports may be combinedwith the Demonstration Planning and Progress Report provided thedata are presented on consecutive pages which may be separatedfrom the basic report. Time histories of all AOA demonstrationmaneuvers shall be Included. A summary of characteristics shallalso be included but shall not replace the time history data.

3.11.2 Sub~Qf reDo r=. Reports 1 isted herein shall besubmitted in accordance wi th the CDRL. Acceptance of reports, orrevisions or additions thereto, or waiv~ng a report or a specifieddemonstration test, shall not be construed to be a waiver of compliancewith the detail specification or any other provision tn the contract.

3.11.3 Beau Ired rerjort$.

3.11 .3.1 Demonstra tion Proaram Plan This is a one time submission.After approval , proposed changes to the plan shal 1 be submitted in theDemonstration Planning and Progress Report.

3.11 .3.2 Demo st ration Plannina and Pros ess ReDortr This reportshal 1 contain comprehensive up-to-date information conce~ning theplanning for the demonstration program, and the relationships betweendenmstrations and other “proof-of-design” requirements and plannedaircraft deliveries. Parts of the report containing the informationspecified in a. through e. shall be submitted concurrently with

99


MI L-D-8708C(AS)

the submittal of the Demonstration Instrumentation Report. Subsequently,at intervals not exceeding two months, additional and/or revised pagesshal 1 be submitted as necessary to furnish as much of the informationspecified in f. through k. as possible and to keep submittal materialup-to-date. If, at the end of any two-month period, added or revisedpages are not necessary to make the report up-to-date, a statement tothat effect shal 1 be submitted. The report shall include the following:

a.

b.

c.

d.

e.

f.

9.

h.

Planned dates for performance of proof-of-design tests and forsubmittal of data, that are prerequi sites for proceeding withvarious demonstration tests.

Planned dates for performance of demonstration tests with each ofthe demonstration aircraft.

Planned dates for DT-11 evaluations by Navy pi lots.

Demonstration schedule for each phase of the demonstration (i .e. ,structural. aerodynamic, propulsion, carrier suitability, etc.).This schedule shall describe the tests to fulfill thedemonstration requirements and the paragraph relationship betweentests and demonstration requirements.

Schedule of aircraft delivery for TECHEVAL, OPEVAL and to theFleet.

Dates of actual performance of the various takeoff, flight,landing, carrier suitabi 1 ity, and ground demonstration testsincluding buildup tests.

Operating limits for flight for contractor and Navy pi lots.

The fol lowing information as applicable:

1.

2.

3.

4.

5.

6.

All structural design gross weights and their derivationusing updated weight data. Also weight, and weightbreakdown and center-of-gravity positions for al 1demonstration configurations.

Aerodynamic and structural design envelopes, and 1 imi ts ofaircraft gross weight versus center-of-gravity position.

Level-flight and limit dive speeds.

Catapult 1 imi t load factor and 1 imi t tow load.

Arresting limit load factor, limit hook drag and side load,and the envelope of design sinking speeds, pitch angles, androl 1 angles for carrier-based aircraft.

Sinking speeds and pitch and roll angles for land basedai rcraft.

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MI L-D-8708 C(AS)

7.

8.

9.

10.

11.

12.

13.

Stall speeds, power-on and power-off, versus gross weight inbasic, landing, and other pertinent configurations.

Determination as to whether Vmax is 1 imi ted by actualstrength, control power, flight character sties, or otherparameters.

Planned flight envelopes for Navy Development Tests.

Landing gear strength envelopes and source or method ofderivation. Such envelopes shall be based on existingstrength as substantiated by tests and supplemented, ifnecessary, by analytical methods.

Curves of aircraft gross weight versus center of gravityposition for extreme aft and forward loadings anddemonstration test loadings.

For each store station, a table listing all the allowablestores, pylons, racks, and their respective weights.

Store carriage design 1 imi t load for take off, landing andflight.

i. Summaries of safe boundaries of flight conditions performedduring flight tests including the following:

1. The test data of equivalent airspeed and Mach number for thereport period shal 1 be denoted as points with appropriatecorrections plotted on design V-n diagrams for sea level andevery ten thousand foot increment of altitude up to theservice ceiling. Information previously reported for eachof the altitudes shal 1 be indicated by shaded areasconnecting their outer boundari es.

2. Information regarding high-speed and low-speed rol 1 Ing pul 1outs (equivalent airspeed and load factor) and high-speedand low-speed steady sides lip (equivalent airspeed andrudder-pedal force) shal 1 be presented in tabular formindicating the most severe maneuvers, shown by flight testto date, that can be safely achieved.

3. A curve indicating the variation of lift coefficient withMach number based on the stall , static longitudinalinstability, undesirable buffet intensity, or othercharacteristics which limit the useful lift capabilities ofthe aircraft. In a like manner, a curve for the aircraftwith stores shall be included.

j. Discussion of any required demonstration tests that thecontractor has concluded cannot be performed in the manner or tothe conditions specified, with ampl i fyi ng information regardingdesign deficiencies involved or other reason for the conclusions.This information shal 1 summarize action taken or contemplated toeliminate the deficiencies and whether or not the contractor is

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MIL-D-8708C(AS)

able to solve design problems posed by the disclosed designdeficiencies.

k. Description of aircraft proposed to be used in the performance ofthe structural demonstration (takeoff, landing, and taxi testsfor land-based and carrier-based aircraft, and dives and pull-outs). If structurally, aerodynamically, and functionallyidentical with aircraft planned to be delivered for TECHEVAL,OPEVAL, and to the F1 eet, a statement to that effect should besubmitted in lieu of detailed descriptions. Otherwise thestructural , aerodynamic, and functional differences shal 1 becompletely described and the effects of these differences on theproof-of-design aspects of’ the structural demonstration shal 1 besummarized. This applies particularly to special provisions indemonstration aircraft which are not to be in service aircraft,such as special cockpit control restrictors; special testinstrumentation, special escape provisions; ballast in lieu ofuseful load, modification to standard stores mounts; and thoseaffecting strength and rigidity, flying qualities, orperformance.

3.11 .3.3 Instrumentation reoorts.

3.11 .3.3.1 Demonstration Instrumentation Reoort. This report shallbe sectionalized by demonstration categories, e.g. , aerodynamics,structures, propulsion, etc. , and shall contain:

a. A complete list of the demonstration items for which eachinstrument will be used.

b. A complete list of variables to be measured with each aircraft,the expected overal 1 accuracy of measurement of each variable,and a discussion of expected errors resulting from time delays orphase shifts between measured parameters.

c. Complete 1 i st of Government-furni shed and contractor-acquiredSpecial Flight Test Instrumentation (SFTI). This list shallidentify the instrumentation as to purpose, function, location,and response character sties requi red.

d. Estimated dates for completing installation of instrumentation ineach aircraft.

e. Oetai 1 ed description of al 1 instrumentation and related systemsand al 1 final calibration data for each aircraft. Thisinformation may be submitted as an appendix to the report nolater than three weeks prior to the time the aircraft isscheduled to arrive at the test site.

f. Sufficient data on the total instrumentation system to ensurethat:

1. No degradation of performance results from extraneous noi se,vibration, shock or temperature.

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MI L-D-8708C(AS)

2. Flat frequency response commensuratebe measured.

with the parameter to

3. Effects of time delays or phase shifts between measuredparameters are commensurate with the accuracy requirementsof the test program.

3.11 .3.3.2 Structural Instrumentation ReDort. This report shal 1contain a complete description, location, and any special calibrationmethod or requirements for each aircraft planned for use in thedemonstration.

3.11 .3.3.3 ~Status Renort This report shal 1 provide the inventory 1 i sting andstatus of Gov~rnment-furni shed and contractor-acquired SFTI in custody ofthe contractor, and shal 1 contain the serial number, nomenclature, modelnumber, range, manufacturer, cost, date equipment was acqui red, presentlocation, aircraft or contract to which assigned, date equipment wasassigned to this contract and current status of each i tern of SFTI.

...

3.11 .3.3.4 SDecial Fliaht Test Instrumentation (SFTI) Excess~. This report shal 1 be submitted at the time theGovernment-owned SFTI becomes excess. Disposition instructions shall berequested. This report shal 1 contain the serial number, nomenclature,manufacturer’s model number, range, manufacturer, cost. date equipmentwas acquired, present location, aircraft or contract to which assigned,date equipment was assigned to this contract and status of each i tern ofexcess SFTI.

3.11 .3.3.5 Sgecial Fliaht Test Instrumentation (s FTI) Requisitionand Technical Rf?DOrt. This report shall include:

a. Requisition and Invoice/shipping Document (OD Form 1149) shall besubmitted when SFTI is initially acquired under the contract andshal 1 contain the contract and program to which the SFTI isassigned, ‘the nomenclature, model number, serial number, range,and date acqui red for each i tern of SFTI. It shal 1 be submittedwhen SFTI is initially acquired under the contract.

b. Documentation on each model of contractor-acqui red SFTI shal 1contain operating procedures, applicable preventive maintenanceprocedures, and physical and performance specifications.

3.11 .3.4 Dailv Fliaht tleDOrtS. Daily reports shal 1 be submitted forthe first 20 flights of each of the first two demonstration aircraftafter which they may be discontinued by the acquiring activity uponrequest. These reports shall be submitted as expeditiously as possibleand within 48 hours after completion of flights, except when additionaldelay is essential to the presentation of data. These reports may bebrief and informal , need not be forwarded by formal correspondence, andshall include the following:

a. Daily flight report number.

103


b.

c.

d.

e.

f.

9.

h.

i.

j.

k.

1.

m.

MI L-D-8708 C(AS)

Model des~gnation.

NAVAIR serl al number.

Contract number.

Oate of flight.

Pilot’s name.

Duration of flight.

Loading condition.

Gross weight.

Purpose of flight (and program If a sertes of flights isinvolved).

Center-of-gravity location.

Changes prior to flight.

Discussion, including pilot observations. concernlna anvphenomena encountered such as unusual or “unexpected-f 1 l~htcharacteristics, yielding or failure of a region of thestructure, flutter including control-surface buzz, or any otherunusual occurrence shall be included. Observations of theoperation of the instal led al rcraft weapon system equipment shal 1be discussed, if applicable.

3.11 .3.5 Bi-Weeklv Sumrnarv ReD orts. These reports shall be briefand Informal and shal 1 contain qual ltative and prel Imlnary quantitativedata (quantitative data for aerodynamic tests only) obtained during thereporting period. If time wi 11 not permit quantitative data obtainedduring the latter part of the reporting period to be included, it shallbe included in the next Bi-14eekly Summary Report, and final data shall besubmttted in the Demonstration Report. The Bi-kleekly Summary Reportshall summarize the purposes of the tests and significant resultsobtained from the tests, including pilot cormnents where applicable.Quantitative data shal 1 be included to cover typical aerodynamic testresults sufficient to define problem areas and/or aerodynamic ccharacter sties not previously reported. The Bi-Weekly Summary Reportshal 1 also describe the configuration of the aircraft includingphotographs and sketches of aerodynamic modifications tested duringthe reporting period. For the duration of the structural dynamic flighttests, separate hi-weekly data reports shal 1 be submitted and prepared i naccordance with MI L-A-8868. Each report shall be submitted not laterthan seven calendar days fol lowing the end of the reporting period.

3.11 .3.6performed oneinclude:

Demonstrate on reDort.i The report shal 1month prior to the date of the report.

104

include all testsThis regort shal 1


MI L-D-8708C(AS)

a. Pertinent data observed or recorded during test. For thestructural demonstration tests, the measured values for eachmaneuver including plotted time-hi story data from ini tiation torecovery. Data shall be plotted within strength envelope plots,data shall be cross-plotted to develop critical load trendInformation, and data shal 1 be plotted verses airspeed andMach number. Complete discussions shall be included of anybuffeting, flutter, excessive vibration, control-surface buzz, orunusual response of the aircraft or component encountered duringthe test. For tests relating to flying qualities, only data fortypical tests conditions shal 1 be presented. The data presentedshal 1 depict trends or support stated conclusions. Summary datashowing variations of stabi Iity and control parameters with Machnumber, altitude, etc. , and compari sons with predictedderivatives shall be presented if available. The data shall bepresented so as to clearly separate demonstration data from otherdata.

b. Conditions of loading.

c. Catapult spotting conditions, when applicable.

d. Arresting conditions, when applicable.

e. Approach speeds, when appl i cable,

f. Engaging speeds, when appl i cable,

9. Changes incorporated.

h. Data obtained during performance’ demonstration tests shal 1 beincluded. Methods and procedures for determination of eachperformance item as we] 1 as related information such as airspeedposition error, ambient temperature, engine thrust, etc. shall beadequately described. Methods and calculations used in thereduction of observed data to standard conditions and in theadjustment of these data to specification conditions shall bepresented.

i . A compilation of the test points and methods employed incalibrating (to 100 percent design limit load) all structuralload, load factor, stress, or temperature measuring devices.

j. Quantitative comparison of the results of dynamic analyses forpredicting time histories of loads and motions, and the maximumloads measured during the land-based and carrier-based takeoff,landing and taxi tests, and the landing gear drop tests. Thecarrier landing tests shall include the superposition of deck-obstruction loads. The foregoing compari son shal 1 be shown inrelation to the strength envelope of the aircraft, such envelopesto be determined by a combination of analyses and static test.These compari sons shal 1 be summarized to show that the aircrafthas structural reliabi lity for the design envelope.

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MI L-D-8708 C(AS)

k. Quantitative compari sons of the measured structural flight test

loads and stresses shall be made with destgn loads and

stresses for the purpose of substantiating critical design loads,load trends, and the analyses baseline. Comparison shall includeboth static and dynamic flight loads. Time histories shall beused where applicable.

1. Quantitative test results and a discussion of the methods used todetermine the accuracy of the weapon delivery system.

3.11 .3.7 .Pre-enqineeri nq reDort. If the bulk of the data requiredprior to Navy DT-11 evaluations has been submitted in the DemonstrationOata Report, a supplemental data report shal 1 be submitted. Otherwise aseparate report shal 1 be submitted for each applicable phase, i .e. , DT-IIA,B, C, etc. , and TECHEVAL.

3.11 .3.8 Structural Demonstration Test Plan. The StructuralDemonstration Test Plan shall include all phases of the structuraldemonstration.

3.11 .3.9 St ructural Dre-fl iqht load survev reDort. This reportshal 1 contain a summary of bui ldup flight tests to date, aircraftconfiguration to be used for the survey, and planned maneuvers andcritical parameters to be surveyed.

3.11.3.10 Structural fliqht loads survey reDort. This report shal 1contain sufficient data to show that the critical components andconditions were tested to the limits for the design. Data from allflight tests shall be included.

3.11.3.11 Structural flic!ht limitations reDort. This report shallcontain the summary of the maneuvers conducted for the structural flightlimitation tests and the structural development flight testing. If testsfrom the structural flight loads survey program are applicable, thereport should so state and present data.

3.11.3.12 Pre-structural demo nstration reoort. This report shallcontain those critical parameters and maneuvers selected from Table ICwith supporting data or” appropriate reference to data from the structuralflight loads survey and flight limitation tests.

3.11.3.13 Structural demonstrations reoort. This report shal 1contain the results of the tests required from Table IC.

3.11.3.14 Structural dvnamic fl iaht demonstration reDorts. Reportsshal 1 be prepared and submitted in accordance with MI L-A-8868 for thestructural dynamic flight demonstration. These reports shal 1 include:

a. Aeroelastic stability, vibration,planning report.

b. Aeroelastic stability flight test

c. Vibration and aeroacoustic flight

106

and aeroacoustic flight test

letter report(s).

test letter report(s).


MI L-D-8708C(AS)

d. Aeroelastic instability, vibration, or sonic-fatigue occurrencereport(s), whenever applicable.

e. Aeroacoustic environment ground test report.

f. Vibration environment measurement report.

9. Aeroacoustic environment measurement report.

3.11.3.15 Struct ural fliaht test a nomal v and fai lure regort. Areport shal 1 be prepared in accordance with MI L-A-8868 and submittedafter a structural flight test anomaly or failure such as overload,fatigue (including sonic or vibration induced), aeroelastic instability,or aeroservoelastic instabi 1 ity has occurred during ground or fl Ighttesting.

3.11.3.16 r r 1 r n 1~ rrier suitabilidemo nstration reDort. The report shal 1 summarize the results of thestructural ground loads and carrier suitabi 1 i ty demonstration.

3.11.3.17 Aer d nami~. This plan shallinclude all phases of the aerodynamic demonstration including theperformance demonstration.

3.11.3.18 Flvina aual i ties demonstration reoort. Thls report shal 1contain quantitative data and qualitative information from the flighttest and demonstration program.

3.11.3.19 Hiah AOA/soin de monstration Sc hedule rer)ort$.

3.11 .3.19.1 Soin de o s tration schedule reoort Thls report shal 1include anticipated spln~i~g character sties based in model tests andanalyses and shall present details of the proposed spin testing program.Those cases where the contractor considers modification to the basic spinprogram to be necessary shall be discussed in this report.

3.11 .3.19.2 ~t This report shal 1summarize the results of the flight test program and include proposedwording for the high AOA/spin information to be presented in the NATOPSFlight Manual . This report shal 1 contain the fol lowing for eachdemonstrated maneuver: gross weight, general arrangement of loading,center-of-gravity, moments of inertia, locations of principal axes, gearand flap position, starting altitude, method of entry, power conditions,turns of spin executed before applying recovery controls, nature of thesteady spin, time per turn, altitude loss per turn, control positions andmaximum forces during recovery, altitude loss in recovery, time histories(from initiation of spin through recovery to level flight) of controlpositions and forces, airspeed, altitude, normal acceleration, angles andrates of pitch, roll and yaw, angles of attack and sides lip. Additionaltime histories of significant buildup maneuvers which the contractorconsiders to be of value to the report shall be Included. The reportshall also describe the emergency spin recovery device includingphotographs.

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MI L-D-8708 C(AS)

3.11.3.20 Performance data-reduction reDort. This report shal 1describe data reduction methods to be used during the aerodynamicdemonstration tests including identification of and procedures forsatisfying proposed performance requirements by mathematical formulationas discussed in 3.3.4.2.1.1.

3.11.3.21 Guaranteed Performance reDort. This report shal 1summarize the individual and cumulative effects on contract guaranteesfor the performance demonstration airplane for:

a. Each change covered by change order or other contract documentand al 1 other pending changes which are under negotiation but arenot yet covered by final contractual action. This includes allchanges, each of which, individual ly, has been determined to have“negligible effects” on contract performance guarantees. TheNAVAIR Aircraft Change Control 8oard number, if applicable, andthe nature of change shal 1 be indicated for each separately1 i steal change.

b. Any change in engine rating.

c. Any overweight or underweight of Government-Furni shed Equipment (GFE).

3.11.3.22 Performance de monstration reDort. This report shal 1present the results of the performance demonstration. Methods andprocedures for determi nation of each performance i tern shal 1 be included.

3.11.3.23 Promslsion svstem de monstration tes t Dlan. This planshal 1 detai 1 the contractor’s proposed demonstration plan.

3.11.3.24 Enqine installation vibration test D lan. This reportshall present a description of the test program planned to demonstratethe vibration characteristics of the power plant installation.

3.11.3.25 Enaine vibration survev recIort. This report shal 1 presentthe results of the power plant vibration survey.

3.11.3.26 Ermine temperature survev reuort. This report shallpresent the results of the power plant temperature survey.

3.11.3.27 Compressor inlet and turbine outlet Dress ure survey-. This report shall present the results of the compressor inlet andoutlet pressure survey.

3.11.3.28 Propulsion Svs tern demonstration reDort. This report shal 1summarize the resul ts of the demonstration.

3.11.3.29 ProDeller vibration survev reDort. This report shallpresent the results of the propeller vibration survey.

3.11.3.30 Armament svstem demonstration test Dlan. This plan shalldetail the proposed demonstration plan.

3.11.3.31 Gunfire vibration and aeroacoustic environment measurementreDort. This report shall present the results of the gun fire vibrationand aeroacoustic envi ronment tests.

108


MI L-D-8708 C(AS)

3.11.3.32 Missile vi bration and aeroacoustlc environ entm. This report shall report the results of the miss!le v!bratio~

easure ent

and aeroacoustic environment measurement tests.

3.11.3.33 Aircraft weaDon Svst em accu racv reoo rt. This report shallcontain quantitative test results and a discussion of the methods used todetermine the accuracy of the aircraft weapon system.

3.11.3.34 Arms ent denmstrat on reDort.m i This report shal 1summarize the results of the demonstration program.

3.11.3.35 Carrier sultabi Iitv d-stration test Qlan and schedulaThis plan shal 1 present the proposed tests to be conducted and a scheduiefor the conduct of the tests.

3.11.3.36 Jet blast deflector acoustic and thermal environment reDo rt.This report shall present the results of the catapult aeroacoustic andthermal environment tests.

3.11.3.37 Fliaht Cent ro 1 Svste m demonst ration reDo rt. This reportshall present the results of the carrier suitability demonstration ofthese systems.

3.11.3.38 Carrier suitab litv demonstration rep.ixt.i This reportshall summarize the results of all phases of the demonstration.

3.11.3.39 Avionic svstem demonstration test DLMIS. These plansshal 1 present the proposed tests to be conducted on the avionic systemand shall include:

a. An Avionic System Performance Demonstration Test Plan.

b. An Avionic System Reliability Demasstration Test Plan.

c. An Avionic System Maintainability Test Plan.

3.11.3.40 Avtonic svste demonstrate ion reDorts These reports shal 1present the results of the a!ionic demonstration te~ts.

3.11.3.41@. This plan shall mpr~se~t th! propo~~d tests to benconducted to

Electro aa et c Co Datibi tv (EMC) demo stration test

demonstrate the electromagnetic compatlbi 1 i ty of the aircraft weaponsystem.

3.11.3.42 Electromaa etic Co D atibilitv ( MC) demonst ation reDorlEThis report shall presentnthe results of the EMC demonstration and shaliidentify those equipments not i n compliance with MI L-E-6051 .

3.11.3.43 Elect icar 1 stration test DIWI This planshal 1 present the proposed tests to be conducted on the electricalsystem.

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MI L-D-8708 C(AS)

3.11.3.44 Electrical system demonst ration reDo rt. This report shallinclude the fol lowing:

a.

b.

c.

d.

Up-to-date copies of al 1 electrical wiring diagrams showing cabledesignations and lengths.

A description of the electrical system operation during normal ,emergency, and ditching procedures.

An electrical load analysis (AC and DC) compiled in accordancewith MI L-E-7016. A description of the instrumentation andprocedures used in conducting the analysis and measurements.

Data, methods, and instrumentation pertaining to the flight andground evaluations of the capabilities of the electrical system.These reports shal 1 contain a comprehensive discussion of theresults obtained and emphasize any operational limitationsimposed by the system design. The discussion and data shall besufficient to judge the validity of the conclusions reached.

3.11.3.45 Instrument svste ms de~ stration Dim.n This plan shallpresent the proposed tests to be conducted on the instrument system.

3.11.3.46 Ument svstems demonst ation renort.r This reportshall present the results of the instrument system demonstration.

3.11.3.47 Crew svstems a d hu an enai eerina demo strat on test Dlann n iThis plan shal 1 present the p~opos~d tests to be conducted in areas of crewsystems and human engineering.

3.11.3.48 Crew svste s and humanm enaineerina demmstrat oni rm.This report shal 1 present the results of the crew systems and humanengineering demonstration tests.

3.11.3.49 Miscellaneous instal ed svstems demo stration test Dlan1This plan shal 1 present the proposed tests to be co~ducted on the “miscellaneous installed systems.

3.11.3.50 MI sce llaneous installed systems re Dort. This report shallpresent the results of the miscellaneous instal led systems demmstration

I tests.

I 3.11.3.51 I n rv~. This plan shall present theproposed tests to be conducted on the icing prevention system.

I 3.11.3.52 Icina survev r@. This report shall present theresults of the icing survey.

3.11.3.53 Reliab ilitv and mai ntat.n abllitv demo stratio test D an1This Dlan shall Dresent the Drollosed tests to be co~ducted !O verifv thatthe reliability and maintainability levels in the detail specificat~onare achieved.

3.11.3.54 Reliability a nd maintainab ilitv dem stration n reDort. Thereport shall contain comprehensive discussion of the results obtained andshal 1 emphasize any operational 1 imitations imposed by the aircraftdesign. The report shall include data, a description of instrumentation,

I I 1.1


I

MI L-D-8708 C(AS)

and methods pertaining to the flight evaluation, testabi 1 itydemonstration results, and a compari son of the results with the BIT/BITE

performance and diagnostic requirements in the detai 1 speci fi cation. Thediscussion and data shall be sufficient to judge the validity of theconclusions presented in the report.

3.11.3.55 Suoo ort demonstration test Dlan. This plan shall presentthe proposed tests to be conducted to verify compliance with the detai 1specification.

3.11.3.56 SUDDOrt d emonstratlon reDort. This report shal 1 presentthe results of the support demonstration.

3.11.3.57 Access or-v eoui Dment de monstration test elan. This planshal 1 present the proposed tests to be conducted on the accessoryequipment.

3.11.3.58 Accessorv eaui Dment d emonstration reDo r~. This reportshal 1 present the results of the accessory equipment demonstration.

3.11.3.59 Svste m safetv demonstration test D lan. This report shal 1present the proposed tests to be conducted to verify that an adequatesafety 1 evel has been achieved.

3.11.3.60 Svst em safetv de monstration reDort. This report shal 1present the results of the system safety demonstration tests.

3.11.3.61 Safetv as ess e t ev t This report shal 1 present theresults of the safety as;ess~e~t ~ad~rl~ accordance with task 209 ofMI L-STD-8B2.

3.11.3.62 Combat s urvivabi 1 i tv demonstration test Dlan. A test planshal 1 be prepared for each survivability demonstration test. Each testplan shall include:

a.

b.

c.

d.

A detailed test description showing how each of the survivabilityrequirement of the detai 1 specification wi 11 be demonstrated.

A cross reference matrix or narrative showing the relationship ofthe requi red demonstration to developmental or verificationtests.

A description of the demonstration criteria and associatedmeasurement methods and specific detai 1s of the test describinginstrumentation, loading, velocities, altitudes, observers, etc.

A detai 1 ed schedule showing demonstration dates and theirrelationship to critical design and other demonstrationmi 1 estones. Test plans shall be cross referenced to theSurvivabi 1 ity Program Plan.

3.11.3.63 Combat survivability demonstration test reDort. Thisreport shall provide, for each individual demonstration, a summary of thetest results, test conditions, significance, conclusions,recommendations, and data gathered.

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MI L-D-8708 C(AS)

4. QUALITY ASSURANCE PROVISIONS

This section is

5. PACKAGING

This section is

6. NOTES

not applicable to this specification.

not applicable to this specification.

(This section contains information of a aeneral or exDlanatorv. . ..—. —.—. ,nature that may be helpful , but 1s not mandatory. )

6.1 ~d USe This specification specifies the testsshal 1 be performed ”for Naval aircraft prior to the TECHEVALperformed by the Navy and certification of readiness forOperational Evaluation (OPEVAL).

6.2 A.caui sition reaui rement~. Acquisition documents mustthe following:

a. Title, number, and date of the specification.

.

which

specify

b. Issue of EY3DISS to be cited in the solicitation, and ifrequired, the specific issue of individual documentsreferenced (see 2.1.1 and 2.2).

6.3 Data eauirements The following Data Item Descriptions(DID’s) sho~n in Tables” VI and VII (see appendix B) must be listed,as appl i cable, on the Contract Data Requirements List (OD Form 1423)when this specification is applied on a contract, in order to obtain thedata, except where DOD FAR Supplement 27.475-1 exempts therequirement for a DD Form 1423. The DIO’S listed in Tables VI andVII were those cleared as of the date of this specification. Thecurrent issue of 00D 501 O,12-L, Acquisition Management Systems andData Requirements Control List (AMSDL) , must be researched toensure that only current, cleared DID’s are cited on the DD Form1423.

6.3.1 Comoletina the C R1.o The types of data listed in Tables VIand VII represent the expec~ed results of investigations and tests usuallyperformed in the development of aircraft weapon systems. The DataItem Description cited Is listed only for guidance in preparing theCDRL and may be substituted. AVOID DUPLICATION OF DATA.

6.4 Definitions. The following definitions are defined for useor reference herel n.

6.4.1 Acti ve cent rol A control system where aircraft motion andcontrol surfaces provide feedback by means other than by directmanual forces to the pilot Input.

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I MIL-D-8708C(AS)

6.4.2 Aircraft/store co Datibllity The abi1ity of the aircraftand stores carried to coe;ist under ;pectfled conditions withoutdetrimental or adverse effects of either upon the aerodynamic,structural, structural dynamics, or functional characteristics ofthe other, including operational or emergency separation of thestores from the aircraft. The specified conditions are usuallythose conditions normally experienced, or expected to beexperienced, by the aircraft involved.

6.4.3 A~ty . Rotational velocity about the respectiveaircraft axis.

6.4.4 I!uWnq. Uncommanded pitching oscillation.

6.4.5 ~. The indicatefJair wedcorrected for installation and instrument errors.

6.4.6 Class fication of aircrafti An aircraft shall be placedin one of the following classes: “

Class I - Small, light aircraft such as:

Light utilityPrimary trainerLight observation

Class 11 - Medium weight, low-to-medium maneuverabi1ity aircraftsuch as:

Heavy utility/search and rescueLight or medium transport/cargo/tankerEarly warning/electronlc countermeasures/airbornecommand, control, or communications relay

AntisubmarineAssault transportReconnaissanceTactical bomberHeavy attackTrainer for Class II

Class 111 - Large, heavy, low-to-medium maneuverabi1ity aircraftsuch as:

Heavy transport/cargo/tankerHeavy bomberPatrol/early warning/electronic countermeasures/alrbornecommand, control or communications relayTrainer for Class III

Class IV - High maneuverability aircraft such as:

Fighter/interceptorAttackTactical reconnaissanceObservationTrainer for Class IV

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MIL-D-8708C(AS)

6.4.7 Contractor’s Dlant. Contractor’s plant is defined as thecontractor’s flight-test facilities.

6.4.8 Control. abruDt diSDlaCf?Mt?ntof. 14herethesespecifications require an abrupt displacement of controls byapplication of a specified force or displacement in a specifiedtime interval, it is not required that hinge moments, power orboost system maximum rates, or maximum displacements as available,be exceeded.

6.4.9 Control. direct lift. That control which provides for avertical translational motion with zero angular velocity oracceleration.

6.4.10 Control. direct side force. That control which providesfor a lateral translational motion of the aircraft with respect toits longitudinal axis.

6.4.11 control force. maximum lateral. That control whichprovides a maximum force in the lateral direction applied normalto the control stick; for wheel control, a couple in the plane ofthe wheel.

6.4.12 control force. maximum longitudinal. This force is alongitudinal pull force applied to the grip of the control stick(wheel) that varies linearly with control position.

6.4.13 Control surface(s) authority. Control surface(s)authority is that combination of active feedback controls thatinvolve a pilot force or programmed displacement input and rate ofpilot force or displacement input to the control surface(s) thatresults in the appropriate aircraft response to perform itsintended maneuver.

6.4.14 Control surface(s) authoritv maximum. That combinationof pilot force or programmed displacement input and rate of pilotforce or displacement input to the control surface(s) that resultsin maximum loads being generated on airframe components during themaneuver for which it is specified.

6.4.15 control surface buzz. Control surface buzz is usuallyevidenced by a pure rotational oscillation of a control surface,or by a torsional windup oscillation when fixity conditions aresuch as to restrain the motion of the surface near one end. Theamplitude of buzz usually increases with an increase in liftcoefficient. Buzz can lead to damage or destruction of the surfaceeither by fatigue or by inducing yield loads when the amplitude issufficiently large.

6.4.16 Control surface resDonse. The aircraft motion resultingfrom changes in control surface position that apply load and hingemoments to the surface as a result of pilot input to the controlsystem.

6.4.17 Critical condition. The design loading condition for whichmargins of safety indicate the structure is most likely to fai1.

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MIL-D-8708C(AS)

6.4.18 Demonstration Droaram coordinate The COMNAVAIRTESTCENis assigned the responsibility, as lead a~~lvity, for thecoordination of al1 demonstrations and for developing, operating,and malntalnlng the NAVAIR Management Information System (MIS) forall aircraft demonstration programs and, in conjunction with otherTest Authoritfes, for reporting current program status to NAVAIR.

6.4.19 OeDarture The event in the post-stall flight regime thatprecipitates entry”into out-of-control post-stal1 gyration, spin,or deep stal1 condltlon. The departure may be characterized bydivergent, large-ampl\tude, uncommanded aircraft motions, such asnose-slice or pitch-up. Oeparture is synonynms with complete lossof control. Departure modifiers are as follows:

6.4.19.1 Susceotlble to deDarture. Departure from controlledflight will generally occur with the application or briefmisapplication of pitch, roll, and yaw controls that may beanticipated in operational use.

6.4.19.2 E,XtreMelV SU5CeDtib e to deDtWtUrR.1 Departure fromcontrolled flight will generally occur with the normal applicationof pitch control alone, or with smal1 rol1 and yaw control inputs.

6.4.19.3 Resistant to deDa tur Departure from controlledflIght wi11 only occur with ~ la~ge and reasonably sustainedmisapplication of pitch, roll, and yaw controls.

6.4.19.4 Extremelv resists t to detIartun re. Departure fromcontrolled f1ight can only occur after an abrupt and inordinatelysustained application of gross, abnormal, pro-departure controls.

6.4.20 m. The term “dive” refers to a flight maneuverexecuted for the purpose of demonstrating strength and rigidityand store separation and release tactics.

6.4.21 Di e aence Divergence is a static aeroelasticinstabi1ityvo~ a 1ifting surface that occurs when the structuraltorsional restoring moment of the surface is exceeded by theaerodynamic torsional moment.

6.4.22 ~ A The true airspeed multipliedby the root of the air density ratio at the altitude concerned.

6.4.23 Flutter. Flutter is a dynamic aeroelastic instability andself-excited osci1lation of an aerodynamic surface. At speedsbelow the flutter speed, oscillations will be damped. At theflutter speed, oscillations will persist with constant amplitude,and at speeds above the flutter speed, oscillations will, in mostcases; diverge and result in damage or destruction of thestructure.

6.4.24 Formal Formal refers to al1 demonstration tests theresults of which indicate that a design requirement has been met,or that the design is suitable for fleet use, or that an item ofequipment operates satisfactorily as part of the aircraft.

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MIL-D-8708C(AS)

6.4.25 Gross weiqht. basic fliqht desicm. For Navy types VT, VP,VS, VAW, V/STOL, and VR, this weight shall be the takeoff grossweight with basic mission useful load. For VA and VF, the basicflight design gross weight shal1 be the weight of the aircraft withbasic mission useful load minus the weight of 40 percent takeofffuel.

6.4..26 Gross weiaht. maximum desian. The maximum design grossweight shall be the weight of the aircraft with maximum internaland maximum external load for which provision is required, with noreductions permitted for fuel using during taxi, warmup, or climb-Out.

6.4.27 Gross weiqht. mlnimum flvinq. The minimum flying grossweight for al1 types of aircraft shal1 be composed of the weightempty plus the items listed below:

a. Five percent of internal fuel (for flying qualities and forflutter and divergence considerations, zero fuel shall alsobe assumed).

b. Oil consistent with 5 percent internal fuel.

c. Minimum crew.

d. No disposable armament or ammunition.

e. No other useful load item.

6.4.28 Hiahest service ceiling. Highest service ceiling is thecei1ing attainable with the use of afterburner or similar poweraugmentation.

6.4.29 Indicated Air SDeed (IASI. The reading of the airspeedindicator uncorrected for instrument, installation andcompressibility errors.

6.4.30 Inert missiles. Inert missiles are missiles withoutexplosive material of any kind such as may be contained in rocketmotors, fuzes, batteries, warheads and target detecting devices.

6.4.31 Inertial Yawina Moment Parameter (IYMP). The terms ofIYMP, Ix - Iymbz are defined as follows:

Ix and I are aircraf moments of inertia about the x and y axis$ 1respecti ely (slug-ft ); m is aircraft mass (slugs); b is wing span

(feet).

6.4.32 Landin.a.asmroach. and takeoff 1imit soeed (VLF1. Thelanding, approach and takeoff 1imit speed is the maximum speed atwhich the landing gear and other devices will be open or extendedfor takeoff or 1anding.

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MIL-D-8708C(AS)

6.4.33 Level fliaht maximum sDeed (V~T~ . The maximum speedattainable at the basic flight design gross weight in the basicconfiguration in level flight with maximum available thrust,including use of afterburners, and rocket thrust augmentationconsidering engine 1imitations, whichever is applicable.

6.4.34 u. The term “limit” used in such phrases as “limitload factor,“ “limit side load factor,” and “limit dive speed”refers to the design limit as specified in the detailspecification.

6.4.35 Load factor n. The ratio of a given load to the weightwith which the load is associated. If employed, a subscriptdesignates the direction of the load.

6.4.36 ~ war ing. That natural aircraft behavioror artificial signal(s) that indicate to the pilot the approach ofloss of control. Stal1 warning and the onset and development ofloss-of-control warning shal1 be described as a function of AOA orairspeed for a given aircraft state. Natural stal1 warning andloss-of-control warning encompass successive AOA ranges.

6.4.37 Maximum safe. The expression “maximum safe load factor(or speed)” means the maximum load factor (or speed) at thespecified speed (or load factor) which can be obtained withoutexceeding the specified limit strength or limits for satisfactorystabi1ity and control, or without experiencing dangerous buffeteffects.

6.4.38 ~maxl. The maximum service speed,Vmax or Mmax, for each altitude is the lowest of:

a. The maximum permissible speed.

b. A speed which is a safe margin below the speed at whichinfol,erable buffet or structural vibration is encountered.

c. The maximum airspeed at MAT, for each altitude, for dives (atall angles) from V~T at all altitude, from which recovery canbe made at 2000 feet above MSL or higher without penetratinga safe margin from loss of control, other dangerous behavior,intolerable buffet, and without exceeding structural 1imits.

6.4.39 ~ d (VpAmin~. The minimum usableairspeed for carrier landings and field carrier landing practice.This speed shal1 be determined by methods approved by NAVAIR. Itshal1 be as demonstrated by appropriate flight tests.

6.4.40-~‘mfa~” ‘he ‘oWest a~rspeed ‘twhich control of the aircraft is poss ble with the critical engine

inoperative.

6.4.41 Minimum control around SDeed (Vmc 1. The lowest speed at!which directional control can be maintaine on the ground when the

critical engine fails during the take-off roll.

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MIL-D-8708C(AS)

6.4.42 Nose slice Uncommanded lateral-directionalmotion viewedby the pilot primarily as a divergence in yaw.

6.4.43 Pitch-uo. Uncommanded, sudden increase in AOA.

6.4’.44 Post-stall. The flight regime involving AOA greater thannominal stall AOA. The aircraft characteristics in the post-stal1regime may consist of several more or less distinct types ofaircraft motion: departure, post-stal1 gyration, spin, and deepstall.

6.4.45 Post-Stall Gvratlon (PSG}. Uncontrolled motion about oneor more aircraft axes following departure. While this type ofaircraft motion involves AOA higher than the stal1 angle, lowerangles may be encountered Intermittently in the course of themotion. When the aircraft motion is other than random about al1axes, a further classification of the PSG may be used fordescriptive purposes. Such terms as snap rol1, rol1ing departure,or tumble may be appropriate; however, they should al1 imply a PSG.The PSG is differentiated from a spin by the lack of a predominant,sustained yawing motion and by the potential for exhibiting sub-stall AOA.

6.4.46 -. The parameter on which engineis based is as follows:

Er!9h.e Power Parameter

Turbojet-fan Net thrust

Turboprop-shaft Shaft horsepowerequivalent shaft

Pulse jet Net thrust

Ram jet Net thrust

Rocket Thrust

performance output

plus thrust orhorsepower

Combination of power plants Use parameters of each applicableengine involved

6.4.47 Recovery. The transition from out-of-control conditionsto control1ed flight. This is normally considered to be thatperiod between pilot initiation of recovery controls and that pointwhen the AOA is at a value below stall and no significant,uncommanded angular motions remain.

6.4.48” Recoverv rol1!s Uncommanded rolling motions near or belowstall AOA that may occu~ during the recovery phase of the spin or PSG.

6.4.49 Recoverv. total altitude. The sum of the altitude lossesduring the recovery and dive pullout.

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MIL-D-8708C(AS)

6.4.50 ~. A sustained yaw rotation of AOAS above stal1. Therotary motions of the spin may have oscillations in pitch, rolland yaw superimposed upon them. The incipient spin is the initial,transitory phase of the motion during which it is not possible toidentify the spin mode. The developed spin 1s the phase of thespin during which it is possible to identify the spin mode. Thefully developed spin is attained when the trajectory has becomevertical and no significant change is noted in the spincharacter sties from turn to turn. Spin modes may be identifiedby average values of AOA and body axis yaw rate and by themagnitude of the three-axis angular oscillations. One modifierfrom each group 1istealin Table 4 may be used to characterize themode.

6.4.51 Stal1 AOA. The AOA for maximum usable lift at a givenflight condition (as defined in MIL-F-8785).

6.4.52 &?lLJkD. An out-of-control flight condition in whichthe aircraft is sustained at an angle of attack well beyond thatfor Alpha (stall) while experiencing negligible rotationalvelocities. The deep stall may be distinguished from a PSG by thelack of significant motions other than a high rate of descent.

6.4.53 StallinciSDeed (VQ. The minimum speed for 1evel flightat sea level in the basic configuration with zero thrust.

6.4.54 ~ eed (VSL1. The minimum speed for 1evel flightin the landing approach configuration with zero thrust.

6.4.55 ~tal1inq sDeed with oower (V$p)-. The minimum speed forlevel flight at sea level in the landlng configuration with thepower or thrust required to provide satisfactory wave-offcharacteristics.

6.4.56 Stall warning. That natural aircraft behavior orartificial signal(s) that indicates to the pilot the approach ofmaximum usable lift. Normally, the onset and development of stal1warning shall be described as a function of AOA or airspeed for agiven aircraft state.

6.4.57 .Stores. The term “stores” means all missiles, rockets,bombs, mines, torpedoes, detachable fuel and spray tanks, pods(refueling thrust augmentation, gun, ECM, etc.) targets, andsimjlar items intended for carriage internally or externally byaircraft, including the racks, launchers, adapters, and pylons usedfor such carriage. This applies whether the items are, or are not,to be separated from the aircraft in flight.

6.4.58 ~. One of the following designated by NAVAIRor COMNAVAIRTESTCEN, as applicable, to witness tests and demonstrations:

a. COMNAVAIRTESTCEN

b. NAVPRO

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MIL-D-8708C(AS)

c. Commander, Commanding Officer or Officer-in-Charge of othersupporting activities.

6.4.59 True Air SDeed (TAS). The speed at which the aircraftmoves through the surrounding air.

6.4.60 Nina rock. Uncommanded lateral-directionalmotion, viewedby the pilot primarily as roll oscillation.

6.5 Swnbols. abbreviations and acronyms. The following symbols,abbreviations and acronyms are defined for use or referenced herein.

AB

ACLS

AFCS

ALSS

AMC

AOA

APCS

APU

ASW

ATE

b

BO

c 1/2

CAo

cc

CDRL

CT

CNA

C.g., Cg

CPS

Afterburner.

Automatic Carrier Landing System.

Automatic F1ight Control System.

Aviation Life Support Systems.

Alternate Mission(s) Configuration(s).

Angle of Attack.

Approach Power Compensator System.

Auxi1iary Power Unit.

Antisubmarine warfare.

Automatic Test Equipment.

Wing span, feet.

Bolter.

Number of cycles for the lateral oscillationsto damp to half amplitude. The inverse ofdamping parameter.

Contract Administration Officer.

Clean configuration.

Contract Data Requirements List.

Catapult takeoff.

Airplane normal force coefficient.

Center of gravity.

Cycles per second.

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MIL-D-8708C(AS)

CR

CRT

o

dB

DID

DPGS

E3

EAS

EMC

EMCON

EMI

FOT&E

FQ&P

FPM

FSED

G

GFP

HERF

HERO

HERP

HPM

IAS

IECMS

ILS

IMN

INSURV

IR

Cruise configuration.

Combat rated thrust.

Oive configuration.

Sound intensity.

Data Item Description.

Data Processing Ground Station.

Electromagnetic environmental effects.

Equivalent alrspeed.

Electromagnetic compatibi1ity.

Emission Control.

Electromagnetic interference.

Follow-on Test and Evaluation.

Flying Qualities and Performance.

Feet per minute.

Full scale engineering development.

Glide configuration.

Government furnished property.

Hazards of electromagnetic radiation to fuel.

Hazards of electromagnetic radiation toordnance.

Hazards of electromagnetic radiation topersonnel.

High power microwave.

Indicated airspeed.

Inflight engine condition monitoring system.

Instrument landing system.

Indicated Mach number.

Board of Inspection and Survey.

Infrared.

121


I

IRT

1ST

JBD

L

LDG)4

M

MI

MT

MAT

M~T

MMRT

Momax

MRP

MSL

NEMP

NRP

nmin

nmax

“Y

nz

NOA

OBOGS

OPEVAL

OPTEVFOR

MIL-D-8708C(AS)

Intermediate rated thrust (maximum non-augmented thrust).

Initial sea trials.

Jet blast deflector.

Landing configuration.

Landing design gross weight.

Mach number.

Moment of inertia.

True Mach number.

Maximum augmented thrust.

Maximum level flight Mach number with maximumaugmented thrust.

Maximum level flight Mach number with militaryrated thrust.

Maximum operational Mach number, as defined bythe maximum operational speed envelope.

Ml1itary rated power.

Mean sea 1evel.

Nuclear electromagnetic pulse.

Normal rated power.

Minimum symmetrical flight 1imit load factor(i.e., the lower boundary of the design V-ndiagram).

Maximum symmetrical flight 1imit load factor(i.e.. the uDDer boundary of the desiqn V-ndiagram).

Side load factor.

Normal 1oad factor

Normal operational asymmetry.

On-board oxygen generating system.

Operational evaluation.

Operational test and evaluation force.

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MIL-D-8708C(AS)

Osc

P

PA

PHAA

PLAA

PMC

@s2V

PSG

Ra+l

RPM

SAS

SIB

SE

SFTI

SFTIP

SOFT

STOL

TAS

T&E

TEMP

TIT

TLF

TNA

TO

Other stores configuration.

Power configuration.

Power approach configuration.

Positive high angle of attack.

Positive low angle of attack.

Primary mission configuration.

The helix angle described by a wing tip duringa rolling maneuver, where:

P= rate of rol1 about the body axis.

b = wing span, feet.

v = true airspeed, feet per second.

Post stall gyration.

Reliability and maintainability.

Revolutions per minute.

Stabi1ity augmentation system.

Speedbrake(s).

Support equipment.

Special flight test instrumentation.

Special flight test instrumentation pool.

Safety-of-flight test.

Short takeoff and landing.

True airspeed.

Test and evaluation.

Test and evaluation master plan.

Turbine inlet temperature.

Thrust for level flight.

Thrust for normal approach.

Takeoff configuration.

123


TPT

VE

‘EAS

VH

VL

‘LF

‘MAT

vmax

‘omax

vmca

vmcg

‘rein

‘MRT

Vs

‘SG

‘SL

‘SPA

‘STO

vVc

Tvc

VTOL

No

MIL-D-8708C(AS)

Tat1pipe temperature.

Engaging speed for arrested landings.

Equivalent airspeed.

Maximum level flight speed.

Limlt speed parameter In basic confIguratlonspecified for structural design.

Landing, approach and takeoff 1imit speed.

Maximum level flight speed with maximumaugmented thrust.

Maximum service speed.

Maximum operational speed, as defined by themaximum operational speed envelope.

Minimum control airspeed.

Minimum control speed, ground.

Minimum service speed.

Maximum level flight speed with militaryrelated thrust.

Stalling speed.

Stal

Stal’

Stal’

ing speed in glide configuration.

ing speed in landing configuration.

ing speed in power approach configuration.

Stal1ing speed in takeoff configuration.

Design sink speed.

Average sink speed.

Vertical takeoff and landing.

Waveoff.

6.6 Sublect term (kev word) listing.

Oetailed program planFull scale engineering developmentHigh angle of attack

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MIL-D-8708C(AS)

6.7 Streamlining. For MIL-D-8708 acquisitions, the required portionsof al1 MIL-D-8708 tier reference shal1 be 1imited to the portionsdescribed in the “Applicability” column in Table X in appendix C.

6.8 ~q. When MIL-D-8708 is tailored in an acquisition, appendix Cmust be tailored accordingly. In particular, when appendix C is tailored,specific attention must be given to the chain of referencing. For example,if a first tier reference document in MIL-O-8708 is tailored out, al1 of thereference documents which are tiered to that first tier reference documentmust be tailored out.

6.9 Chanqes from Drevious issue. Marginal notations are not usedin this revision to identify changes with respect to the previousissue due to the extensiveness of the changes.

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MIL-D-8708C(AS)

APPENDIX A

CONTRACTOR DEMONSTRATION REQUIREMENTS FOR NAVY DEVELOPMENT TESTS

10. SCOPE

10.1 ~. This appendix defines the general scope and purposeof Navy Development Tests and the contractor demonstrations thatshal1 be completed prior to conducting each phase. This appendixis a mandatory part of this specification. The informationcontained herein is intended for compliance.

20. APPLICABLE OOCUMENTS

This section is not applicable to this appendix.

30. NAVY OEVELOPMENT TESTS

30.1 OeveloDment tests. At appropriate periods during Ful1 SealeEngineering Development (FSEO), a team of Navy pilots, engineers,technicians and maintenance personnel, wi11 initiate Navydevelopment tests, which consist of dedicated ground and flighttests by the test team to evaluate the aircraft design at variousstages of development. The initial OT-IIA evaluation will beperformed subsequent to the inspection of the aircraft and at theearliest practical point in the demonstration program. Additionalevaluations such as OT-IIB, OT-IIC, etc., will be performed, asrequired, at times related to the demonstration program when theallowable envelope is increased, when new systems/equipment areincorporated, or when changes are incorporated to correctdeficiencies. The final phase of OT-11 is the formal technicalevaluation (TECHEVAL) to assure readiness for OPEVAL.

30.2 Objectives. The objectives of Navy Development Tests areto:

a. Identify and allow early correction of deficiencies.

b. Evaluate changes incorporated.

c. Perform an early assessment of the aircraft in the shipboardenvironment.

d. Demonstrate that the aircraft meets the specification andcontract guarantees.

e. Establish a basis for certification of readiness for OPEVAL.

30.3 ScoDe of tests.

30.3.1 OT-IIA. Within the allowable flight envelope, theevaluation will consist of:

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MIL-D-8708C(AS)

APPENDIX A

a. Installation and functional ground and flight tests of allinstalled and operating equipment in the demonstrationalrcraft to the extent appropriate to the stage of developmentof the aircraft.

b. Evaluation of longitudinal, lateral, and directional stabilityand control flying qualities at a normal weight andcorrespond ng c.g. as follows:

1.

2.

3.

4.

5.

6.

7.

8.

9.

Taxi and ground handling character sties.

Takeoff character stics, including cross-wind evaluation.

Climb, cruise, maneuvering, and descent characteristics,including effects of speed brake, power, andconfiguration changes.

Transonic and supersonic characteristics including trimand stabi1ity changes when decelerating through sonicspeed at a high load factor.

Buffet and vibration in flight.

Control character sties with alternative and/or emergencysystems in operation.

Low-speed characteristics, including stalls, waveoff andnormal and moderate crosswind landings.

Carrier-approach character sties, for carrier types.

Other items that may be specifically reauested by theacquiring activity.-

c. Performance evaluation of items in this specification for theparticular model aircraft which include:

1.

2.

3.

4.

5.

6.

7.

Takeoff and landing distances and speeds for normalservice operation.

Maximum rate of climb and combat cei1ing.

vMax at high and low altitude.

Acceleration and deceleration.

Stall speeds in various configurations.

Field carrier landing practice approach speeds (whereapplicable).

Mission profile and prelIminary cruise control.

127

,-


MIL-D-8708C(AS)

APPENDIX A

30.3.2 DT-IIB and subsequent evaluations. These evaluaconsist of:

a.

b.

c.

d.

e.

f.

30.

ions wil

Re-evaluation of those character sties that are affected byaircraft changes instal1ed since completion of priorevaluation(s).

Evaluation of those iternsplanned to be performed in priorevaluation(s) that were not completed.

Evaluation of the items of DT-IIA at critical combinations ofaircraft weight and e.g.

Evaluation of the aircraft for the expanded envelope andfurther investigation of character stics not fully evaluatedpreviously.

An Initial Sea Trials (1ST) may be conducted prior to TECHEVALby NAVAIRTESTCEN pilots to obtain an early assessment of theaircraft in the shipboard environment. Only normal landingsand take-offs wi11 be performed. The 1ST may be combined withthe ACLS Sea Trials if practical. A shore based buiid-upphase wi11 be conducted prior to the Sea Trials to ensure thatthe aircraft is suitable for limited carrier operations.

ACLS Sea Trials (ACLS/ST) may be conducted prior to TECHEVALby NAVAIRTESTCEN pilots to obtain an early assessment of theACLS performance in the shipboard environment. A shore basedbuiId-up phase wi11 be conducted prior to the Sea Trials toensure that the ACLS is suitable for 1imited carrieroperations.

3.3 TECHEVAL. TECHEVAL is the final phase of DT-11 and isconducted WIth production representative hardware and validatedsoftware to identify technical deficiencies and determine whetherthe design meets technical specifications and contract guaranteesfor certification of readiness for OPEVAL. TECHEVAL is conductedat critical combinations of aircraft weight and e.g. and includes:

a. Re-evaluation of those character sties that are affected byaircraft changes installed since completion of prior DT-11evaluations.

b. Evaluation of aircraft to the limits of the specified flightenvelope (repeating only those items affected by any expansionof the flight envelope).

c. An evaluation of the aircraft weapon system installation,which includes but is not necessarily limited to thefollowing:

1. Functional and accuracy checks of cwn. bomb. rocket.guided missile, fire c~ntrol, and ;ther armamentinstallations, systems, and equipment; photographic,electrical, and avionic equipments.

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MIL-D-8708C(AS)

I

APPENDIX A

2. F1ight tests of tracking characteristics and gunneryruns.

3. Flight tests of fire control systems and firing runs ata suitable target.

4. Flight tests of guided missile control systems, includinglaunch and guidance to intercept or impact on a suitabletarget:

5. Suitability of control of external stores and storedrops. The quantlty, types of stores, and loadconfiguration will be as specified in the detailspectficatlon.

40. CONTRACTOR DEMONSTRATION REQUIREMENTS

40.1 Contractor d monstration. The contractor shal1 configure thetest aircraft for e~ch DT-11 evaluation as approved for the demonstrationprogram or as agreed upon during the applIcable Pre-DT-11 conference.Installed instrumentation shal1 not be changed from that used bythe contractor unless specifically requested by the cognizant TestAuthorlty. It shall have been shown by fllght tests prior to theDT-11 evaluations and by other data, if required, that within theallowable flight envelope, the aircraft is aerodynam!cally,andaeroelastically stable, and structurally and functionally safe forthe tests to be performed by Navy pilots.

40.2 Pre-DT-II enai~ina data Data substantiating theproposed envelopes and recommended initial evaluation operatingllm!ts shall have been submitted at least two weeks prior to theapplicable pre-DT-11 evaluation conference. Prior to initiationof DT-11 evaluations, the acquiring activity will have authorizedrelease of the aircraft and established the initial operatinglimits for Navy test pilots.

40.3 InsoectIon. A complete inspection of the aircraft and Itscomponents shall be accomplished prior to initiation of DT-IIA.The scope of this inspection shal1 be as approved during the Pre-DT-IIA conference. The contractor shal1 perform the inspection,and it will be witnessed by representatives of the Test Authority.

40.4 ProDosed fliaht envelooes The flight envelopes proposedfor the DT-IIA, DT-IIB, and subsequent evaluations shall be definedin the first and subsequent Demasstratlon Planning and ProgressReports. Prior to evaluation flights by Navy pilots, sufficientflight tests shall have been performed to establish the permissiblefllght envelope. The flight envelopes shall be sufficient topermlt an adequate evaluation of the iternsof 30.3.1 and 30.3.2 forDT-IIA, DT-IIB, and subsequent evaluations.

40.5 Reau remei nts orior tg~. Prior to TECHEVAL, thefollowing demonstrations shall have been completed:

129


a

b

c.

MIL-D-8708C(AS)

APPENDIX A

Structural build-up tests specified in Tables IA and IB shallhave been completed within the required service flightenvelope. Data from tests may be used to satisfy the formalstructural demonstration tests in Table IC or ID, asapplicable.

Land-based and carrier-based takeoff, landing and taxi tests.For carrier-based aircraft, the tests include.only fieldlanding and takeoffs.

Structural dynamic f1ight tests.

d. Aerodynamiccs demonstrations as follows:

1. Flying qualities tests within the service flightenvelope.

2. Maximum permlssible speed envelope.

3. Spin build-up tests.

e. Propulsion system tests.

f. Al1 armament svstem software shal1 have been valida~ed and thefollowing test; completed:

1. Ground and flight functionalequipment.

2. Firing of guns and rockets.

3. Guided missile demonstration.

tests of all installed

4. Droppable stores tests.

5. Armament control tests.

9. Al1 avionic system hardware and software shal1 have beentested.

h. Crew system demonstration.

40.6 Requirements orior to 1ST or ACLS/ST. When 1ST or ACLS/STare conducted prior to TECHEVAL the following additionaldemonstrations shal1 have been completed:

a. Prior to commencement of the build-up phase for 1ST, thecontractor shal1 have:

1. Satisfactorily completed the steam ingestiondemonstration (exhaust gas ingestion for VSTOL aircraft).

2. Satisfactorily completed the jet blast deflectordemonstration.

130


MIL-D-8708C(AS)

APPENDIX A

3. Made sufficient progress in the conduct of the carriersuitability catapult launch and arrested landingstructural demonstration (landing structuraldemonstrations for VSTOL aircraft) to ensure adequatestrength during shipboard operation of the loading(s) andconfigurations to be tested.

4. Completed the EMV/EMI survey.

5. Corrected those deficiencies identified during earlierDT-11 phases which require correction prior to 1ST.

b. Prior to the commencement of the ACLS/ST the contractor shal1have:

1. Conducted the ACLS Simulation evaluation.

2. Conducted the ACLS ground demonstration.

3. Conducted the ACLS airborne subsystem flight functionalcheck demonstration of the ACLS radar augmenter, ILSreceiver, data link installation (including theassociated antennas), and the ACLS and ILS displays(discrete and flight path error data).

4. Conducted the ACLS open loop flight demonstration.

5. Conducted the ACLS closed loop flight demonstration.

6. Corrected those deficiencies identified during earlierDT-11 phases that require correction prior to ACLS/ST.

50. CONFERENCES

50.1 Pre-DT-11 conferences. Prior to the initiation ofdevelopment test phases OT-IIA (and subsequent) and TECHEVAL,conferences shall be held to review the results of all ground andflight tests accomplished prior to that phase. The extent to whichthe test requirements have been satisfied within the authorizedenvelope shal1 be reviewed and the configuration of the aircraftto be available for the specific DT-11 phase and the extent towhich support will be required will be defined.

50.2 Post DT-11 conferences. Following the availabi1ity andreview of reports of the DT-11 development tests, conferences shal1be held to review corrective action taken or recommended to betaken on each deficiency reported during these phases and todiscuss an effectivity date or production number for correctiveaction.

131


MIL-D-8708C(AS)

APPENDIX B

SCHEDULE OF DATES FOR SUBMISSION OF REPORTS AND FOR CONFERENCES

10. SCOPE

10.1 x. The purpose of this appendix is to provide an easyreference to the dates for submission of reports and for theconvening of conferences. This appendix is not a mandatory part of theSpecification. The information contained herein is intended forguidance only.

20. APPLICABLE DOCUMENTS

This section is not applicable to this appendix,

30. TABLES OF REPORTS SUBMISSION/CONFERENCECONVENING DATES

132


TABLE VI.

ReDOrt name

DemonstrationProgramPlan

Structural

Structural

~:~:;~ural

~:~g;;ural

Structural

InstrumentationReport

DemonstrationTest Plan

Pre-Flight Load Survey

FlightLoads Survey

F1ight LimitationsReport

Pre-StructuralDemonstrationReport

ReDorts Schedule and data item description.

Referencearaaraoh

3.11.3.1

3.11.3.3.2

3.11.3.8

3.11.3.9

3.11.3.10

3.11.3.11

3.11.3.12

Da s Da s Da sDIO ngm~er before before dand first fliaht m

a er l??r to@ EVAL

DI-NDT$i~Kl~89 .120$%?gdures)

DI-T-30728(Instrgment?tion

30

& CallbratlonReport)

DI-NDTI-80566(Test Plan)

90

01-S-30591(Oata and/or

60

AnalysisSummary)

DI-S-30591 45(~:~~y;~~lor

Summary)

DI-S-30591(~;~ g~dlor

45

Summ{ry!

DI-S-30591 45

%#$’or


TABLE VI. morts schedule and data item descriDti~ -Continued.

Wort na eReference

m ~ DI; ~~~~gr ]~%[ef,iaht Mre

Structural DemonstrationsReport 3.11.3.13 DI-T-2072(Reports, Test)

Aeroacoustic EnvironmentGroundTest Report 3.11.3.14e DI-T-2072

(Reports, Test)V~j~;}on EnvironmentMeasurement 3.11.3.14f 01-T-2072

(Reports, Test)A~~~rm;~usticEnvironmentMeasurement 3.11.3.14g 01-T-2072

(Reports, Test)Aerodynamic DemonstrationTest Plan 3.11.3.17 DI-NOTI-80566

(Test Plan)F~{)in~tQualities Demonstration 3.11.3.18 01-T-2072

(Reports,Test)PerformanceOata ReductionReport 3.11.3.20 01-MISC- 0711

f(Scienti ic andz Technical Reports)&Guaranteed PerformanceReport 3.11.3.21 01-T-2072

(Reports,Test)

30

60

60

60

90

15

90

30


TABLE VI. Re~orts schedule and data iterndescriotion- Continued.

ReDort namq

PerformanceDemonstrationReport

PropulsionSystem DemonstrationTest Plan

En ine InstallationVibrationTestPTan

Engine Vibration Survey Report

Engine TemperatureSurvey Report

Compressor Inlet and TurbineOutletPressure Survey Report

P~:::};ion System Demonstration

Propeller Vibration Survey Report

Reference D;: n~m erarauravh t t!e !l!kflidt !&- !!&

3.11.3.22 DI-T-2072(Reports,Test)

60

3.11.3.23 ?+~~~TJi~~j66 60

3.11.3.24 DI-NDTI-80566 60(Test Plan)

3.11.3.25 DI-T-2 72?(Repor s, Test

60

3.11.3.26 DI-T-2072(Reports, Test)

60

3.11.3.27 DI-T-2 72?(Repor s, Test)

60


60

3.11.3.29 DI-T-2 72?(Repor s, Test)

60

Days

MM!

w

.


-— —

TABLE VI. ReDorts schedule and data item descTiDt\On - Continued

wm

Revort nam~

Afl~yent SystemDemonstrationTest

Gunfire Vibrationand AeroacousticEnvironmentMeasurementReport

MissjIe Vibrationand AeroacousticEnvlronmentMeasurementReport

Aircraft IleaponSystemAccuracyReport

Armanment DemonstrationReport

Carrier SuitabilityDemonstrationTest Plan and Schedule

Jet 31ast DeflectorAcoustic andTherzal EnvironmentRepart

A;CS~$gCS/ACLSDemonstration

~~~o;~ SuitabilityDemonstration

ReferenceDaraaraDh

3.11.3.30

3.11.3.31

3.11.3.32

3.11.3.33

3.11.3.34

3.11.3.35

3.11.3.36

3.11.3.37

3.11.3.38

Da sD~~ n~m~er

Oa sbeforefirs

be;oret fiiqht @

DI-NDTI-80566 90(Test Plan)

DI-T-2072(Reports,Test)




DI-NDTI-80566(Test Plan)


01-T-2072(Reports,Test)


Oa sf!

Oaysa er@ w

60

60

60

90

60

6(I

60

60


TABLE VI. Reoorts schedule and data item description- Continued.

Re!Jort nam~

A}\h~;c System Demonstration,Test

A[~~g~~sSystemDemonstration

ElectromagneticCompatibility(EMC)DemonstrationTest Plan

ElectromagneticCompatibility(EMC)DemonstrationReport

E}:;{r~fa~ System Demonstration

E~;j_;\cal System Demonstration

In trument Systems DemonstrationPlan

~ I~;s.~~ent Systems Demonstration4

C~~~~{~:~fo~n$e~~~~a~ngi neering

L-

PreferenceparaaraDfi

3.11.3.39

3.11.3.40

3.11.3.41

3.11.3.42

3.11.3.43

3.11.3.44

3.11.3.45

3.11.3.46

3.11.3.47

Da sOID n~m er

Da s

!?

Oa st))~ore be;ore da er

and tlt fliaht @ @

01-NOTI-80566 60(Test Plan)


60

01-EMCS-80201. 60

l;l%$%%~e+~~t Plan)


60

01-NOTI-80566 60(Test Plan)


DI-NOTI-80566 60(Test Plan)


01-HFAC-80743(Human EngineeringTest Plan)

60

60

Days

w

60

P-0-umz0

x.w


TABLE VI. Rmorts schedule and data Item desc iotlar - Continued.

Da s Da s

Reoort name ~ Z! !~~~~r W!OW &re ErReference

C~gno; stems and Human Demonstration 3.11.3.48i

DI-T-2072 60(Reports,Test)

Miscellaneous Installd Systemsf

3.11.3.49 01-NDTI-80566 60Demonstration Test P an (Test Plan)

Miscellaneous InstalledSystems 3.11.3.50 01-T-2072 60Report (Reports,Test)

Icing Survey Test Plan 3.11.3.51 01-NDTI-80566(Test Plan)

60

Icing Survey Report ““ 3.11.3.52 01-T-2072 60(Reports,Test)

Reliability and Maint inability{?Oemonstra ion Test P an

3.11.3.53 01-NDTI-80566 60(Test Plan)01-MNTY-808 1

u ia

(Maintainab lity/TestabilityDemon. Test Plan)

Reliability and Maintainability!

3.11.3.54 DI-T-2072 60Demonstra ion Report

‘f:fivA:doi!{t)(Maintainab ity/TestabilityDemon. Test Report

>-u-umza

Ew


TABLE VI. ReDorts schedule and data iterndescriDtion - Continued.

Da sbefore

Da s Da sReference DID ngmber before ~

Days

ReDOrt name paraqrao fitREvE

Support DemonstrationTest Plan 3.11.3.55‘ ;;$;;:;oj,, ‘“S’ ‘liaht % w _

Support DemonstrationReport

Accessor EquipmentDemonstrationTest Pl{n

A~;~~~~ry EquipmentDemonstration

S ternSafety DemonstrationTest$i’an

System Safety DemonstrationReport

Safety Assessment Report

Cfin~tp :~ivability Demonstration?

Combat Survivabi11ty DemonstrationTest Report

S ecial Flight Test Instrumentation!nventory and Status Report


3.11.3.57 DI-NOTI-BO66(Test Plan!


3.11.3.59 01-NDTI-8066(Test Plan?


3.11.3.63 01-T-2072(Reports,Test)

3.11.3.3.3 DI-MGMT-80441(Govt Pr P rtyPhysica’?!nvent r

Rl::c%K;?!?af

60

30

60

60

60

90

D-0

1%z

60

Annually as of 30 May


TABLE VII. R r~e ubmission at

ReDort name

Demonstration Planningand Progress

Demonstration InstrumentationReport

Special Flight Test Instrumentation(SFTI) Excess EquipmentReport

S ecial Flight.Test Instrumentation

!{~~~~ Requlsltlonand Technical

Daily Flight Reports

zo Bi-Weekly SuurnaryReports

Referenceparaaraoh

3.11.3.2

3.11.3.3.1

3.11.3.3.4

3.11.3.3.5

3.11.3.4

3.11.3.5

DI-MISC-IJ711“f(Scien~lIC &

TechnicalReports)

DI-T-30728(Instrum~ntat~onand Cal~bratlonReport)

01-MISC-80348(Reportof ExcessEquipment)

DI-MGMT-80441(GovernmentPropertyPhysical

#~#~{ R!!ic:r

Hhen submitted

At intervalsnot exceedingtwo months

When SFTI becomesexcess

When SFTI is initial

O 11 for at leas t}f!lg{tsof qach Q t

demonstrationalrcr

Every two weeks

y acquired

e fjrst 20e first twoft

Ii


TABLE VII. b orts ith no fixed submissiondatg - Continued.w

DemonstrationReport

Aeroelastic St bility Vibration?and Aeroacout c F1igfitTest

Planning Report

Aeroelastic Stability Flight TestLetter Report(s)

Vibration and AeroacousticFlightTest Letter Report(s)

Aeroela tic Instability,Vibrationfor Son c FatigueOccurence Report(s)

A

Structural Fli ht Test Anomaly andFailure Repor?

Structur 1 Ground Load and Carrier!Suitabi?ity Denmstra ion Report

Reference DID number

3.11.3.6 DI-MISC- 0711!(Scienti ic &

~:;gdl~:~l

3.11.3.14a 131-NDTI-8088(Test Plans7Procedures)

3.11.3.14b 01-T-2072(Reports,Test)

3.11.3.14c DI-T-2072Reports, Test)

3.11.3.14d DI-MISC- 711!CScienti ?C &

TechnicalReports)

3.11.3.15 DI-MISC-80711

%%#c &

3“’’”3”” !f;~%fi~~f’i

Reports

At intervalsnot greater than twomonths beginning with the firstr vision of the DemonstrationP!anning and Pro ress Report

!following first light

9 days before start of instrumentation?o airplane

7 a s after en of each hi-weekly!fl!g{t test per od

7 da s after end of each hi-weeklyfligl!ttest period

$~~~fl~s!?{?[!!~b?!!!$~n%n?: %{igue ~ .:

ground;?lifi~e~~g:sivevibration in ,: +m30 days after a structural anomaly or ~ ~failure is experienced %= 0m ~

~~#~5~:~tf~r:g~f~;~~gg! l?tydays fter the struct r 1 ground


MIL-D-8708C(AS)

APPENDIX B

TABLE VIII. Conference schedule

Daysbefore first

Conference name .W

Instrumentation Planning Conferences 550

Structural F1ight Load Survey PlanningConference

Structural Flight Demonstration PlanningConference

Structural Ground loads and CarrierSuitabi1ity Demonstration PlanningConference

Structural Dynamic F1ight DemonstrationPlanning Conference

Performance Data-Reduction ProceduresConference

High AOA and Spin Demonstration PlanningConference

Performance Demonstration PlanningConference

Flying Qualities Demonstration Conference

Avionics Demonstration Conference

Daysbeforetestldemo

60

30

180

30

1BO

30

120

30

180

142


MIL-D-8708C(AS)

APPENDIX 8

TABLE IX. Conference with no fixed convenlna date.

conference name When convened

Structural Instrumentation Planning One month after submlttalConference of the structural

instrumentation report

Pre-DT-11 Conferences Prior to DT-IIA and subsequentevaluations as scheduled by theacquiring activity or the TestAuthority

Following the availabi1ity andreview of the results of theDT-IIA and subsequentevaluations when scheduled bythe acquiring activity or theTest Authority

Post-DT-11 Conferences

143


MIL-D-8708C(AS)

APPENDIX C

STREAMLINING INFORMATION

10. SCOPE

10.1 =. This appendix is a list of documents referenced inMIL-D-8708 or tiered to documents referenced in MIL-D-8708. Thesedocuments have the same status as those referenced directly inMIL-D-8708 (first tier documents). This appendix is a mandatory partof this specification. The Information contained herein 1s intendedfor compllance.

10.2 ~. This append’ixdocuments referenced in MIL-D-8708MIL-D-8708 through the third tier.listed in Table X of this appendixcolumn, is pertinent in the use ofIn acquisition, this appendix must

20. APPLICABLE 00CUMENTS

identifies the applicability of theor tiered to documents referenced inOnly that portion(s) of a document,and described in the “Applicability”MIL-O-8708. If MIL-D-8708 is tailoredalso be tailored.

20.1 OocumentS. The documents listed herein and correspondingapplicability data have been identified as required. All other documentsreferenced through tiering are not considered required and may be used forguidance and information.

144


TABLE X. Reauired documentsand corresoondina aooIicabilitvdata

DOCUMENTNUMBER: DOCUMENT TITLE:

First Tier (1 of 96 i)ocumentsl

MIL-E-5007 Engine,Aircraft,Turbofan, Generalfor

~’

APPLICABILITY: REFERENCEDBY:

Turbojet and Demonstrationof inletair MIL-D-8708Specification 9ressurevariation:enaine

conditioningments.

Al1 secondand third tler references, tiered to MIL-E-5007,are for

First Tier (Z o f 96 Oocuments)

monitorin~require-

guidanceand information.

zz

MIL-S-8512m Support Equipment Aeronautical, Pneumaticsystems, MIL-O-8708 >?Special,General Specification hydraulicand pneumatic

-umyfor the Design of systempressure test.

mZWO-J

s?c~nd Ti@~

.0XC9

nn c

MIL-P-8721O Pneumatic Power Systems, HighG

Pneumaticsystems. MiL-S-35i2Replaces PressureMIL-P-5518

The remainingsecondtier references, tiered to 141L-S-8512,are for guidanceand information.

Third Tier

Al1 thirdtier references,tiered to MIL-S-8512,are for guidanceand information.


TABLE X. R ired d urnnts and orresequ oc e c Dondinq aoolicabilitv data (continuedl.

DOCUMENT NUMBER: DOCUMENT TITLE:

First Tier (3 of 96OocumentQ

MIL-B-5087 Bonding, Electrical and LightningProtection, for AerospaceSystems

S?cznd Tier

AN960 Washer, Flat

AN935 Washer - Lock, Spring

MS35;38 Washer, Lock-Spring,Helical,(Replaces Regular (Medium) SeriesMS35337)

MS35340 Hasier, Leek-Spring,Helical,(Regiacss Extra DutyMS35339)

/4S25083 Jumper Assembly, ElectricBondingand Current Return

AN735 Clamp, Loop Type Bonding

TT-L-32 Lacquer,Cellulose Nitrate,(Replaces Glass for AircraftHIL-L-6706)

APPLICABILITY:

Requirementsand qua]ity assurance.

Entiredocument.

Entlre document (for use whentemperaturedoes not exceed4009F).

Entire document (for use whentemperature’does exceed400”F).

Entiredocument (for use whentemperaturedoes exceed400”F).

in~,re document (for use whentemperaturedoes not exceed300”F).

Requirementsfor CRES and aluminumplumbingonly; zinc platingpro-hibited

Clear lacquer.

REFERENCED

MIL-D-8708

MIL-8-5087

141L-B-5087

HIL-B-5087

HIL-8-5087

MIL-8-5087

MIL-8-5087

MIL-8-5087

8’f:

Al1 remainingsecond tier references,tiered to MIL-8-5087,are for guidanceand information.


TABLE X. Reauired documents and corresDondina aoDlicabi1ity data (continued).

DOCUMENT NUMBER:

Third Tier

MIL-S-7952

MIL-S-5059

QQ-A-25015

QQ-B-613

W-P-416

MIL-A-8625

MIL-C-5541

MIL-C-13924

W-P-35

Q$B-746

DOCUMENT TITLE:

Steel, Sheet and Strip UncoatedCarbon (1020 and 1025) (AircraftQuality)

Steel, Corrosion-Resistant(18-B)Plate, Sheet and Strip

Aluminum Al10Y ALCAD 2024, Plateand Sheet

Brass, Leaded and Non-Leaded,FlatProducts (Plate, Bar, Sheet andStrip)

Plating, Cadmium (Electrodeposited)

Anodic Coatings, for Aluminum andAluminum Al10YS

Chemical ConversionCoatings onAluminum and Aluminum Al10YS

Coating, Ox’{de,Black, for FerrousMetals

PassivationTreatmentsforCorrosion-ResistingSteel

Bronze, Phosphor; Bars, Plates,Rods, Shapes, Sheets and Strips

APPLICABILITY:

Carbon steel.

Requirements.

T3 or T4.

Composition 1 or 2.

Type II, Class 2

Requirements.

Class 3.

Class 3 or 4.

Requirementsfor uncoated CRESonly.

Composition A.

REFERENCED BY:

AN960

AN960

AN960

AN960

AN960

AN960

AN960MS25083

AN960

AN960AN735MS35338

AN935


TABLE X. Reauired documents and corresoondinqaDtIliCabilitV data (continued)

DOCUMENT NUMBER:

Q-C-591

QQ-P-416

FED-STD-595

MIL-S-5059

zmAMS 5510

ASTM A380

FED-STD-66

QQ-B-750

QQ-N-286

MIL-P-16232

DOCUMENT TITLE:

Copper Silicon, Copper ZincSilicon and Copper Nickel SiliconAlloys, Rod, Wire, Shapes, Forgingsand Flat Products

Plating, Cadmiurn(Electrodeposited)

Colors

Steel, Corrosion-Resistant(18-8),Plate, Sheet and Strip

Steel Sheet, Strip and Plate,Corrosion and Heat Resistant,18Cr-10.5Ni-.4TiSolution,HeatTreated

Cleaning and Descaling StainlessSteel Parts, Equipmentand Systems

Steel, Chemical CompositionandHardenabi1ity

Bronze, Phosphor, Bar, Plate, Rod,Sheet Strip, Flat Wire andStructuraland Special ShapedSections

Nickel-Copper-AluminumAl10Y,14rought

Phosphate Coating, Heavy,Manganese or Zinc Base (forFerrous Metals)

APPLICABILITY:

Class A, Composition hard.

Type III, Class 3.Type II, Class 2.

Color Number 23538.

302 CRES steel.

Technical requirementsand qualityassurance sections.

Cleaning and descaling sections.

C106O to C108O steel.

CompositionA, conditionhard.

Class A.

Type Z, Class 2.

REFERENCEDBY:

AN935

AN935MS35338

AN935MS35338

AN735

AN735

AN735

FK35338

MS35338

14S35338

MS35338


TABLE X. Reauired documents and correspondingaoDlicabi1itv data (continued~.

DOCUMENT NUMBER:

MIL-C-13924

MIL-I-17214

QQ-A-22512

WW-T-700/2

m-A-250/2

MIL-I-23053/5

ASTM B172

MIL-T-7928

DOCUMENT TITLE:

Coating, Oxide, Black, for FerrousMetals

Indicator,Permeabi1ity, Low-Mu(Go-No-Go)

Aluminum Alloy Bar, Rod and Wire,Rolled Drawn or Cold Finished,3003

Tube, Aluminum Al10Y, Drawn, Seam-less, 1100

Aluminum Alloy 3003, Plate andSheet

InsulationSteering, Electrical,Heat Shrinkable, Polyolefin,FlexibleCrosslinked

Standard Specificationfor Rope-Lay-StrandedCopper ConductorsHaving Branched-StrandedMembers

Terminal, Lug and Splice, Crimp-Style, Copper

APPL1CA81L17Y:

Class 4.

Magnetic permeabilityof 2 maximum;field strengthof M=200.

Temper O.

Temper O.

Temper O.

Class 2, clear, heat shrinkable.

Classificationand requirementsfor wire sections.

Any QPL item.

REFERENCED BY:

MS3533B

MS3533B

MS250B3

MS25083

MS250B3

MS25083

MS250B3

MS250B3

The remainingthird tier references, tiered to MIL-B-5087,are for guidance and information.


TABLE X. Reauired documentsand corresoondinq aollIicabilitvdata (continued)

m0

DOCUMENT NUMBER: DOCUMENTTITLE:

First Tier (4 of 96 Document~~

MIL-11-5088

Second Tier

MIL-STD-1388

MIL-F-7179

MIL-STO-454

MIL-S-8516

MIL-S-Z3586(1)

MIL-N-ZZ759

HSI41OO

MIL-T-81490

Hiring,Aerospace Vehicle

LogisticSupport Analysis

Finishes,Coatings, and Sealants

StandardGeneral RequirementsforElectronicEquipment

SealingCompound, PolysulfideRubber ElectricConnectorsandElectricSystems, Chemically Cured

SealingCompound, Electrical,SiIi,coneRubber, AcceleratorRequired

Hire, Electric,Fluropolymer,Insulated,Copper or CapperAlloy

Tape Identification,CoaxialCable,TransmissionLine Assembly

TransmissionLines, TransverseElectromagneticMode

APPLICABILITY:

Electricaland protectionsystemsrequirements.

RAM goals for the wiring system.

Requirementsectiononly formetals.

Requirement16, DissimilarMetals;Requirement“5,Soldering.

Any QPL item.

Any QPL item.

Any QPL itern.

Hire identification

Any QPL itern.

REFERENCE BY:

MIL-O-8708

MIL-W-5088

HIL-N-5088

MIL-H-5088

KIL-N-5088

MIL-N-5088

MIL-W-5088

HIL-it5088

MIL-W-5088


I

0-!

TABLE X, Reauired documents and corresDondin~ aDDlicabilit~data (continued.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY: REFERENCEDBY:

MIL-STD-704 Aircraft Electric Pawer Charac- Voltage drop for power distribu- MIL-W-5088istics tion circuits.

MIL-C-85485 Cable, Electric, Filter Line, Any QPL itern. MIL-W-50BBRadio Frequency Absorptive

MS25274 Cap, Electrical (Wire End Crimp Caps for use on undesignated MIL-W-5088StYle. TYDe II. Class 1) for wire ends.10~”C”To~al Conductor Temperature

MIL-E-6051 ElectromagneticCompatibility MinimumRequirements

MIL-C-7762 Compasses, Installationof Maximum

EMI requirement’s. MIL-W-5088

~

allowable compassdeviation.

MIL-S-23190 Straps, Clamps, and Mounting Hard- Any QPL itern. MIL-W-5088 - ~zware, Plastic for Cable Harness l-lTying andSupport

s:

MS21919

MS25281

MIL-T-43435

MIL-I-23594

MS90387

Clamps,,LoopSupport

Clamp, Loop,

Tape, Lacing

Type, Cushioned Wire support. MIL-W-5088

Plastic, Wire Support Wire support. MIL-W-5088

and Tying Requirementsand quality assurance. MIL-W-5088

InsulationTape, ElectricalHigh Type 1. MIL-W-5088Temperature,Polytetrafluroethy-lene, Pressure-Sensitive

Tool, Hand, Adjustable for Plastic Installationtool for plastic MIL-W-5088and Metal Tiedown Straps straps.


G1N

DOCUMENT NUMBER:

MIL-I-7444

MIL-I-631

MIL-I-3190

MIL-I-3190(ReplacesMIL-I-18057)

MIL-I-3190(ReplacesMIL-I-18057)

MIL-I-23053

MS25171

t4S35489

MS21266

TABLE X. Reauired documents and corresoondina a!xllicab~litvdata (continued~.

00CUMENT TITLE:

InsulationSleeving, Electrical,Flexible

Insulation,Electrical, SyntheticResin Composition,Nonrigid

InsulationSleeving, Electrical,Flexible,Coated, General Spec-ification for

InsulatingSleeving, Electrical,Flexible,Treated

InsulationSleeving, Electrical,Flexible,Coated, Class 200, TypeO, Category C

InsulationSleeving, ElectricalHeat Shrinkable,General Specif~-cation,for

Nipple, ElectricalTerminal

Grommets, Synthetic and SiliconeRubber, Hot-Oi1 and CoolantResistant

Grommet, Plastic Edging

APPLICABILITY:

Requirementsand quality assurance

Any QPL

Any QPL

tern.

tern.

Any QPL itern.

Any QPL item.

First article requirementsandquality assurance.

Requirements.

Requirements.

Requirementsfor permanentbondedgrorunets.

REFERENCE BY:

MIL-W-5088

MIL-W-508B

MIL-W-50BB

MIL-W-50B8

MIL-W-5088

MIL-W-5088

MIL-W-50B8

MIL-W-508B

MIL-W-508B

>v-umlzu.x

n


TABLE X. R ir d umen s n~ data ntinuedl.

u!L.J


MIL-S-83519 Splice, Shield Termination,SolderStyle, Insulated, Heat Shrinkable,EnvironmentResistant, GeneralSpecificationfor

MIL-C-6136 Conduit: Electrical, Flexible,Shielded,Aluminum Alloy for Air-craft Installations

MIL-B-50B7 Bonding, Electrical and LightningProtection,for Aerospace Systems

MIL-C-39029 Contacts, Electric Connector,General Specification for

MIL-C-22520 CrimpingTools, Terminal, Hand orPower Actuated, Nire Terminationand Tool Kits, General Specifica-tion for

MIL-C-3607

MIL-C-3650

MIL-C-3655

Connectors,Coaxial, Radio Fre-quency,,Series Pulse, GeneralSpecificationfor

Connectors,Coaxial, Radio Fre-quency,Series LC

Connector,Plug and Receptacle:Electrical(Coaxial, Series Twin)and Associated Fittings, General

‘ Specif~cationfor

APPLICABILITY:

Any QPL itern.

Requirementsand quality assurancefor use when rigid conduitsareimpractical.

Conduit grounding.

Any QPL itern.

Any QPL item.

Requirementsand quality assurance.


Any QPL itern.

REFERENCEDBY:

MIL-W-50BB

MIL-I’I-50BB

MIL-W-50BB

MIL-W-50BB > ~-07Lm~

MIL-W-50B8 ~ :x%

,,n G:

MIL-W-5088

t41L-14-5088

MIL-W-50B8


TABLE X. Reauired documents and corresDondinq aoDlicabilitvdata (continued).


MIL-C-26637

MIL-C-25516

MIL-C-39012

MS33540

MIL-M-24041

MS27488

MIL-B-7883

MS90376

NAS813

NAS820

Connectors, Coaxial, Radio Fre-quency, Series LT, GeneralSpecificationfor

Connector, Electrical,Miniature,Coaxial, Environment ResistantType, General Specificationfor

Connectors, Coaxial, Radio Fre-quency, General Specificationfor

Safety Hiring and Cotter Pinning,General Practices for

Molding and Potting Compound,Chemically Cured Polyurethane(PolyetherBased)

Plug, End Seal, ElectricalConnector

Brazing of Steels, Copper, CopperAlloys, Nickel Alloys, Aluminumand Aluminum Al10YS

Caps, Dust, Plastic, ElectricConnector

Cap - Protective, ElectricalConnector

Plug - Protective, ElectricalConnector

APPLICABILITY: REFERENCED BY:

Requirementsand quality assurance. MIL-W-5088

Any QPL itern.

Any QPL itern.

CRES wire.

Any QPL item.

Requirements.


Oust caps.

Dust caps.

Dust caps.

MIL-W-5088

MIL-W-508B

MIL-W-50B8 x

MIL-W-5088

MIL-W-508B

MIL-W-5088

MIL-W-508B

{

[


DOCUMENT NUMBER:

MIL-C-85049

MIL-T-7928(2)

MIL-S-81824

MIL-T-7099

TABLE X. Reauired documents and corresDondina aoolicabilit~ data (continued).

MS25439

t41L-T-81714/11

MIL-T-81714/12

MS18029

MIL-T-81714

DOCUMENT TITLE:

Connector Accessories, Electrical,General Specification for

Terminal, Lug and Splice, CrimpStyle, Copper

Splice, Electric, Permanent,CrimpStyle, Copper Insulated,Environ-ment Resistant

Terminal, Lug and Splice, CrimpStyle Aluminum, for Aluminum Air-craft Hire

Splice - Permanent Crimp Style,2 Way Type for Aluminum AircraftWire, Class 1

Terminal Junction System Splice,Single

Terminal Junction System Splice,Double

Cover Assembly, Electrical,forMS27212 Terminal Board Assembly

Terminal Junction Systems, GeneralSpecificationfor


Any QPL itern. MIL-W-50B8

Any QPL itern. MIL-W-50BB

Any QPL

Any QPL

tern. MIL-W-50BB

tern. MIL-W-50BB

Aluminum conductor splices.

Any QPL itern.

Any QPL itern. MIL-14-5088

Requirements. MIL-W-5088

Any QPL item. MIL-W-5088

The remainingsecond tier references, tiered to MIL-W-SOBB,are for guidance and information.


TABLE X. Reauired documents and corresDondina aDDlicabilitvdata (continued).


Third Tier

MIL-F-18264

MIL-S-5002

MIL-STD-104

InalMIL-STD-l05

FED-STD-601

ASTM D746

ASTM D786(3)

Q-C-576

~A-250/4

Finishes,Organic, Heapons Systems,Application and Control of

Surface Treatments and InorganicCoatings for Metal Surfaces ofWeapon Systems

Limit for Electrical InsulationColor

Sampling Procedures and Tables forInspectionby Attributes

Rubber, Sampling and Testing

BrittlenessTemperatureof Plasticsand Elastomersby Impact

CelluloseAcetate Plastic Sheets

Copper Flat Products With S1it,S1it and Edge Rolled, Sheared,Sawed or Machine Edges (Plate, Bar,Sheet and Strip)

Aluminum Alloy 2024, Plate andSheet

APPLICABILITY:

Application of organic finishes;Table II requirements;coatingrequirementsfor interiorandexterior finishes.

Metal surface treatments.

Insulation color for Type IIIsleeving.

Level 111, AQL of 2.5%.

Method 4111, Tensile strength;Method 2021, Thickness;Method4121, Elongation;Method 14011,Specific Gravity.

Procedures for testingat 67”C.

Dielectric with air as surroundingmedium.

Copper plate.

Any QPL item.

REFERENCE BY:

MIL-F-7179

MIL-F-7179

MIL-I-7444

MIL-I-7444

t41L-I-7444

MIL-I-7444

MIL-I-7444

MIL-I-7444

MIL-I-7444


TABLE X. R uir d d umen anea e oc ts d corresoondinaaDDlicabilitv (codata ntinuedl.

DOCUMENT NUMBER:

TT-S-735

FED-STD-595

MIL-T-9906

ASTM D4066(ReplacesMIL-M-20693)

MIL-A-8625

MIL-S-23190

22-R-765(ReplacesMIL-R-5847)

ASTM 01457(ReplacesL-P-403)

ASTM D21161(ReplacesL-P-389)

MS20995

DOCUMENT TITLE:

Standard Test F1uids, Hydrocarbons

Colors

Tape, Identification,AerospaceVehicle, Tubular Marking

Standard Specification for NylonInjection and Extrusion Material

Anodic Coatings, for Aluminum andAluminum Alloys

Straps, Clamps and Mounting Hard-ware, Plastic for Cable HarnessTying and Support

Rubber, Si1icone

Standard Specification for Poly-tetrafluorethyleneMolding andExtrusion Materials

Standard Specification for Fluor-ocarbonMolding and ExtrusionMaterials

Wire, Safety or Lock

APPLICABILITY:

Type VI.

Color numbers 37144 and 17038.

Any QPL itern.

CompositionA, Type 1.


Any QPL

Class 2,

tern.

Grade 50.

Procedures.

Procedure section.Table I requirements.

Safety wire requirements.

REFERENCEDBY:

MIL-I-7444

MS141OO

MS141OO

MS252B1MS21266

MS25281x~%

MS90387 ~ ~z:ax :nn

MS25171 :w

MS21266

MS21266MIL-I-23594

MS33540


TABLE X. Reauired documents and corresoondinc!aoolicabilitvdata (continued

DOCUMENT NUMBER:

t41L-P-19468

EIA RS 359

MIL-STD-1344

L-P-390

MIL-T-7928

MIL-STD-105

FED-STD-191

ASTM D792

ASTM D1”49(ReplacesFED-STD-406,Method 4031)

00CUMENT TITLE:

Plastic Rod, Polyetrafluroethylene,Molded and Extruded

Standard Colors for Color ID andCoatlng

Test Methods for ElectricalConnectors

Plastic Molding and ExtrusionMaterial, Polyethelyneand Copoly-”mers (Low, Medium and High Density)

Terminal Lug and Splice, CrimpStyle Copper

Sampling Proceduresand Tables forInspectionby Attributes

Textile Test Methods

Standard Test Methods for SpecificGravity (RelativeDensity) andDensity of Plastics by Displacement

Standard Test Method for DielectricBreakdownVoltage and DielectricStrength of Solid ElectricalInsulatingMaterials

APPLICABILITY:

Any QPL itern.

Colors.

Method 3003. Insulationresistance

Type I, Class L, Grade optional.Type I, Class ‘L,Grade 1.Type I, Class L, Grade 1.

Any QPL item.

Inspection level S-3 and AQL of4.0%.

Method 5030, Thickness averageof 5 to .001 in.; Method 4102,Elongation/Breakageaverage of5 to 0.2% and .5 lb; Method 5651,Colorfastness;Method 2611, Maxcontent; Method 5760, FungusResistance; Method 5852, Aging.

Method A.

REFERENCEDBY:

MS27488

MS2748B

MS27488

MS90376NAS820NAS813

x

MIL-I-23594

Summary of test methods, acmaratus, 141L-I-23594hazards and sampling sections.


p

{

1’TABLE X. Wi red docum~nd rr Ina amlicabilitv data (continued).

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILI~: REFERENCEDBY:

ASTM 0570 Standard Test Methods for Water Condftioning,procedureand re- MIL-I-’23594(Replaces Absorptionof Plastics conditioningsections.FED-STD-406,Method 7031)

MIL-STD-105 Sampling Procedures and Tables InspectionlevelS-3; AQL of 2.5%. MIL-I-23594for Inspection by Attributes

The remainingthird tier references, tiered to MIL-W-5088,are for guidanceand information.

(1) t41L-li-8516is the preferredmaterial.(2) Do not use for Navy application splicing.(3) ASTM D786 is canceledwith no supersedingdocument.

xFirst Tier (5 of 96 DocumW >7-0 +:MIL-E-5372 Fuse, Current Limiter Type, Vibratory stresssurvey rsquire- MIL-D-8708 ~ ~

Aircraft ments (groundand flignt tssts). z gn

~..n sw

All secondand third tier references, tiered to MIL-E-5372,are for guidanceand information.

first Tier (6 of 96 Documw

MIL-E-5400 ElectronicEquipment,Aerospace, ~~e~~~;d ambienttemperature MIL-O-8708General Specificationfor . . .

d and Third Tiers.

All secondand third tier references, tiered to MIL-E-5400,are for guidanceand information.


TABLE X. Reauired documents and corresoondinq aoolicabilitvdata (continued~

DOCUMENT NUMBER: DOCUMENTTITLE: APPLICABILITY:

First Tier (7 of 96 Documents>

REFERENCEDBY:

MIL-T-5522 Test Requirementsand Methods Requirementsand qualityassurancefor Aircraft Hydraulicand includingaccessibilityand suit-EmergencyPneumaticSystems abi1ity of externalconnections.

First Tier (8 Of 9b Documental

MIL-C-5809 Circuit Breakers,Trip-Free,Air- Any QPL itern.‘craft,General Specificationfor

Second and”Third Tierszo Al1 secondand third tier references,tieredto MIL-C-5809,are for guidanceand information.

First Tier (9 of96 Documents)

t41L-T-58.12 TransparentAreas on Aircraft Complianceof defoggingsystem. )41L-D-8708Surfac?s (Windshieldsandcanc~ies),Rain Removingandk(ash~ngSystems for Defrosting,Deicing,Oefogging,GeneralSpecificationfor

MIL-O-8708

MIL-O-8708

HIL-STD-21O Climatic Informationto Determine Ambient atmosphereconditions: MIL-T-5842Design and Test Requirementsfor 10% risk criteriarequirements.Mi1itary Systems and Equipment

The remainingsecondtier references,tieredto HIL-T-5842,are forThird Tier

HIL-STD-81O EnvironmentalTest Proceduresand Test methodsEngineeringGuidelines conditions.


for atmospheric HIL-STO-210

The remainingthird tier references,tiered to MIL-T-5842,are for guidanceand information.


TABLEX. R ir d d ument nd orr~ Iicabilitvda ntinued),


First Tier (10 of 9b Documents)

liIL-E-6051

Second Tier

MIL-STD-704

MIL-B-5087

m

MIL-C-5

MIL-F-15733

MIL-STD-461

MIL-STD-462

MS90298

ElectromagneticCompatibi1ityRequirements,Systems

Aircraft Electric Power Character-istics

Bonding, Electrical, and “LightningProtection for Aerospace Systems

Capacitors, Fixed, Mica-Dielectric,General Specificationfor

Filters and Capacitors,RadioFreq Interference,General Spec-ification for

ElectromagneticEmissionandSusceptibilityRequirementsforthe Control of ElectromagneticInterference

ElectromagneticInterferenceCharacter sties, Measurementsof

Connector, Receptacle,ElectricConnector

APPLICABILITY: REFERENCEDOY:

IntrasystemEMC and EMI general MIL-D-8708requirementsfor Naval acquisitions.

Electricalpower requirementsments includingsurges,ripples,voltages, etc.

Bonding and groundingprovisionsincludingbases and fixedsites:lightningprotectionrequirements.

Any QPL item.

Any QPL itern.

Subsystems/equipmentdesign.requirements;predictedproblemareas.

Subsystems/equipmentdesignrequirements;predictedproblemareas.

Grounding jack.

MIL-E-6051

MIL-E-6051x

>7-0Q+MIL-E-6051 : ~

H gx nMIL-E-6051 n :

MIL-E-6051

MIL-E-6051

MIL-E-6051


TABLE X. ~i red documents and correspondina~ icabilitvdata (continued).

‘DOCUMENTNUMBER:

MS33645

USAS Cl

MIL-STD-454

MIL-STD-1385(ReplacesMIL-P-24014)

MIL-C-11693

mN

MIL-C-889

MS25384

DOCUMENTTITLE:

Receptacle,Grounding, Instal-lationof

NationalElectricalCode

StandardGeneral RequirementsforElectronicEquipment

Preclusionof Ordnance Hazards InElectromagneticFields; GeneralRequirementsfor

Capacitors,Feed Through, RadioInterference,Reduction,AC andDC (HermeticallySealed in MetallicCases),General Specificationfor

Capacitors,By-Pass, Radio Inter-ference,Reduction, PaperDielectric,AC and DC (HermeticallySealed in Metallic Cases), GeneralSpecificationfor

ElectrostaticDischarger Jumper,Fuel Nozzle-to-Aircraft

APPLICABILIl_f: REFERENCEDBY:

Ground jack installation MIL-E-6051compliance.

Groundingat bases and fixed sites. MIL-E-6051

Requirement1, Safety Design MIL-E-6051Criteria; Requirement5, ElectricalOverload Protection.

P~ovisions to protect subsystems MIL-E-6051from inadvertentignitionordudding caused by electromagneticor electrostaticenergy.

Any QPL item.

Any QPL item.

Plug forcables.

The remainingsecondtier references,tiered to MIL-E-6051, are

MIL-E-6051

MIL-E-6051

groundingand bonding .MIL-E-6051

for guidance and information.


TABLE X. Reauired documents and corresr)ondinaaDDliCabilitV data (continued).

DOCUMENT NUMBER:

Third Tier

AN960

MS25082

QQ-B-613

w-0-750

W-P-41 6

MS3943

MIL-STO-1O5

FED-STD-595

MIL-B-5087

MIL-STD-1385

MIL-STD-1377

DOCUMENT TITLE:

Washer, Flat

Nut, Plain, Hexagon, Electrical-Thin

Brass, Leaded and Non)eaded: FlatProducts (Plate, Bar, Sheet, Strip)

Bronze, Phosphor; Bar, Plate, Rod,+Sheet, Strip, Flat hire, andStructural and Special ShapedSections


Connector, Plug and Cap Electric,Grounding

Sampling Proceduresand Tablesfor Inspectionsby Attributes

Colors

Bonding, Electricaland LightningProtection,for Aerospace Systems

Preclusionof Ordnance Hazards inElectromagneticFields, GeneralRequirementsforEffectivenessof Cab}e, Connectorand Weapon EnclosureShieldingand Filters in PreclusionHazardsof ElectromagneticRadiation toOrdnance, Measurementof

APPLICABILITY:

Al alloy untreated washer.

Brass oxide plated nut.

Brass rect for sleeve.

CompositionA.

Type II, Class .?.

Test plug; insertionand removalforces, life expectancy.

Inspection level

Color No. 33538,

S-2; AQL of 1%.

37038.

Installationof receptacle.

Requirementsfor systems orsvstems utilizinq electro

sub-

e~plosive device;.Effectivenessof cablesshields and ,filters.

connectors,

REFERENCEDBY:

MS90298

MS90298

MS90298

MS9029B

MS90298

MS90298

MS90298

MS33645

MS33645

MIL-STO-461

MIL-STO-461


I

TABLE X. Reauired documents and corres~ondinq aooIicabilitv data (continued~,

00CUMENT NUMBER: 00CUMENTTITLE: APPLICABILITY: REFERENCE BY:

MIL-STO-462 ElectromagneticInterference Test proceduresfor EMI. MIL-jTO-461Characteristics,Measurementof

The remainingthird tier references, tiered to MIL-E-6051, are for guidanceand information.

First Tier (1I of 96 Oocuments~

MIL-I-6115

Second Tier

c1* AN5811

AN5812

AN5813

MIL-A-8625

WW-T-70014(replacesNW-T-787)

AN6270

TT-S-1732(ReplacesJAN-A-669)

14S33656

InstrumentSystems, Pitot Tubeand Flush Static Port Operated,Installationof

Tube, Pitot, ElectricallyHeated,“L” Shaped, Inverted

Tube, Pitot, ElectricallyHeated,“L” Shaped

Tube, Pitot, ElectricallyHeated

Anodic Coatings for AluminumandAluminumAlloys

Tube, Aluminum Alloy, Orawn,Seamless

Hose Assembly-DetachableSwivelFitting,Low Pressure

Sealing Compound; Pipe Joint andThread, Lead Free, General Purpose

FittingEnd, Standard Dimensionsfor Flared Tube ConnectionandGasket Seal

Requirementsand qualityassurance. MIL-O-8708

x

Requirements. MIL-I-6115 ~ r-00-,

Requirements.,,

C-J sm

Requirements. MIL-I-6115

Anodic film requirements. MIL-I-6115

Requirementsand qualityassurance. MIL-I-6115

F1exible hose and connection MIL-I-6115requirements.

Anti-seizecompound requirements. IIIL-I-6115

Drain fitting requirements. MIL-I-6115


(

TABLE X. Reauired documents and corresgondinqapplicabilitydata (continued).


AN929-4 Cap Assembly, Pressure Seal Flared -4 assembly; requirements. MIL-I-6115Tube

ANDIO41O(1) Pitot Static and Pitot Tube - Wirina diaoram requirements MIL-I-6115Niring Diagram for (elec~ricajcircui’tfor tubes

with heater elements).

The remainingsecond tier references, tiered to MIL-I-6115, are for guidance and information.

) AND1041O has been canceled with no supersedingdo~ument.

Third Tier

MIL-C-5541

MIL-STD-l05

ChemicalAluminum

Sampling

Conversion Coatings onand Aluminum Al10YS

Procedures and Tables for

ASTM B137

ASTM B244

Inspectionby Attributes

Standard Test Methad for Measure-ments of Weight of Coating anAnodicailyCoated Aluminum

Standard Test Method for Measure-ment of Thickness of AnodicCoatings on Aluminum and OtherNon-ConductiveCoatings on Non-magnetic Metals

FED-STO-I51 Metals, Tests Methods

ASTM B117 Standard Test Method of Salt Spray(Replaces (Fog) TestingMethod 811 ofFED-STD-151)

Class 1A, brush applications.

Inspection level 2, AQL of 1.5%.

Specimens and proceduressections.

MIL-A-8625

MIL-A-8625

MIL-A-8625

Specimens and proceduressections.

Method 520.

Apparatus, salt solution,con-ditions in chamber, period andcontinuityof test and evaluationsections.

MIL-A-8625

MIL-A-8625

NIL-A-8625


I

DOCUMENT NUMBER:

ASTM G23

ASTM D822

FED-STD-141mm

ASTM D2244

ww-T-7oo/GEN

TABLEX. Reauired documentsand corresDondinq aDolicabilitvdata (continued).

DOCUMENTTITLE:

StandardPractice for OperatingLight Exposure Apparatus (CarbonArc Type) Hith and WithoutWaterfor Exposureof Nonmetal1icMaterials

StandardPractice for OperatirigLight and Water ExposureApparatus(CarbonArc Type) for TestingPaint and Related CoatingsandMaterials

Paint, Varnish, LacquerandRelatedMaterials;Methods forTestingof

StandardMethod for CalculationofColor Differences for Instrumen-tallyMeasured Color Coordinates

Tube, Aluminum and AluminumAl10Y,Orawn. Seamless. General Specifi-cation for


General proceduresand Methods MIL-A-8625l,2and3.

Procedures,exposureand evaluation MIL-A-8625of resultssections.

Method 6192. 141L-A-8625 x>~-uv?mz~

Summary of method and procedure MIL-A-8625 ~ ~sections. l-ln Gm

Flattening,pressure,electro- HW-T-700/4magnetic tests and qualityassurance.

The remainingthirdtier referenced,tiered to MIL-I-6115, are for guidanceand information.

First Tier (12 of 96 Oocuments)

i+IL-D-6728 Oampers; Engine ExhaustFlame Testand Glass

Second and ThirdTiert

Al1 secondand thirdtier references,tiered to MIL-O-6728,

procedurefor flamedamping. llIL-O-8708

are for guidanceand information.


TABLE X. Reauired documentsand corresoondina ai)olicabilitv data (continued

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY: REFERENCEDBY;

First Tier (13 of 9b Documents}

NIL-H-6729 Watertightnessof Aircraft, Requirementsand qualityassurance HIL-D-8708Testing, General Specification of ground and flight aircraftfor watertightnessof all systems.

Second Tier

S0-8706 General Specification for Design Watertightnessinvestigations MIL-W-6729Examinations,Engineering,Air- and analyses:test and inspectioncraft Neapon Systems procedures.

NAVAIR 01-lA-509 Aircraft !4eaponsSystems,Clcaning Cleaning procedurefor the water- MIL-W-6729 _xm4 and Corrosion Control tightnesstest. >~

70

The remainingsecond tier references,+

tiered to MIL-W-6729,are for guidanceand information. =$a.n

Third Tier

MIL-T-22085 Tape, Pressure Sensitive,Adhesive, Any QPLPreservationand Sealing

MIL-8-131 Barrier Materials,Waterproof, Any QPLFlexible,Heat Sealable

t~ .

tern.

x= n(l s

NAVAIR01-IA-509 u

NAVAIR01-lA-509

TT-N-95 Naptha Aliphatic Requirements. NAVAIR01-IA-509

The remainingthird tier references,tiered to MIL-H-6729,are for guidanceand information.


TABLE X. Reauired documentsand corresoondinaaDDlicabiIitv data (continued).

DOCUMENT NUMBER: DOCUMENTTITLE: APPLICABILITY:


MIL-L-6730

Second Tier

MIL-E-7080

MIL-N-50B8

MIL-L-6723mm

MIL-C-25050

t41L-STD-d10(ReplacesHIL-E-5272)

MIL-STO-461

MIL-L-21652

MIL-L-81174

LightingEquipment,Exterior,Air-craft (GeneralRequirementsfor)

ElectricEquipment,Aircraft,Selectionand [nstailationof

Hiring, AerospaceVehicle

Lights,Aircraft,GeneralSpec-ificationfor

Color, AeronauticalLightsandLightingEquipment,GeneralRequirsments for

EnvironmentalTest MethodsandEngineeringGuidelines

ElectromagneticEmissionandSusceptibilityRequirementsforthe Control of ElectromagneticInterference

Light, Beacon.Anticollision,Air-craft, General Specificationfor

Lights, Landing,Aircraft,Retractablee

Requirementsand qualityassurance.

Exteriorlightingequipmentand-controlsinstallation.


Any QPL itern.

Exteriorlightingrequirements(aviationcolors).

Environmentalrequirements.

Radio interferencerequirements.

Any QPL item.

Any QPL item.

REFERENCEDBY:

MIL-O-8708

MIL-L-6730

MIL-L-6730

MIL-L-6730

t41L-L-6730

MIL-L-6730

MIL-L-6730

HIL-L-6730

MIL-L-6730


TABLE X. Reauired documents and corresoondinqal)plicabilitydata (continued).


MIL-A-19736 Air Refueling Systems, GeneralSpecification for

MIL-I-18079 Installationof Angle of Attackand Sideslip Systems

MS25318 Light, Approach, 28 V

MS25219 Light-Navigationaland Warning,Aircraft

MIL-C-6781 Control Panel: Aircraft EquipmentRack or Console Mounted

MIL-F-26301 Flashers, Aircraft Navigational(Replaces Light, General Specification forMIL-F-7929)

There are no additionalsecond tier references.

Third Tier

MIL-L-6723 Lights, Aircraft, GeneralSpecification for

MIL-L-18276 Lighting, Aircraft Interior;Installationof

MIL-STO-462 ElectromagneticEmissionandSusceptibility,Test Methods for

MIL-C-25050 Color, Aeronautical Lights andLighting Equipment,GeneralSpecificationfor

MIL-STD-81O EnvironmentalTest Methods andEngineeringGuidelines

APPLICABILITY:

Requirementsfor refueling andtanker signal lights.

Requirementsand quality assurancefor approach Iight system.

Requirements.

Type 1683 lamp.

Control switch requirements.

Any QPL itern.

Any QPL item.

Naval aircraft lighting.

Emission limit requirements.

Identificationcolor.

Method 514, Vibration;Method 516,Shock; Method 513, Acceleration.

REFERENCEDBY:

MIL-L-6730

MIL-L-6730

MIL-L-6730

MIL-L-6730

MIL-L-6730

MIL-L-6730

MIL-E-7080

MIL-E-7080

MIL-STD-461

MS25318

MS25318

AlI remainingthird tier references, tiered to MIL-L-6730, are for guidance and information.


TABLEX. Reauired documentsand corres~ondinq aDg]icabilitv data (continued~.


First Tier (15 of 96 t)ocuments~

MIL-E-7016 ElectricLoad and Power SourceCapacity,Analysis of

First Tier (16 of 96 Oocuments~

.I0

MIL-E-7080

second Tier

MIL-F-7179

ASTM D495(ReplacesL-P-406)

HIL-STO-810(ReplacesMIL-E-5272)

MS90298

MS33645

MIL-B-5087

MIL-E-6051

MIL-I-6181

ElectricalEquipment;Aircraft,Selectionand Installationof

finishes,Coatings, and Sealantsfor the Protectionof Aerospace!4eaponSystems

StandardTest Method for HighVoltage, Low Current Ory ArcResistancefor Solid ElectricalInsulation

Environmental,ProceduresandEngineeringGuidelines

Connector,Receptacle,ElectricConnector

Receptacle,Grounding, Instal-lationof

Bonding,Electrical, and LightningProtection,for AerospaceSystems

ElectromagneticCompatibilityRequirements,Systems

InterferenceControlAircraft Equipment

Requirements,

APPLICABILITY:

Preliminaryload analysisrequire-ments.

Requirements,and qualityassuranceexcept for selection.

Finish and coating requirementsfor electricalsystems.

Apparatus,safety, conditioningand procedurefor determiningarcresistancetime.

Explosionproof tests.

Entire document.

Entire document.

Jumper wire requirementsforvialingcurrent returnpaths.

InstaIIationrequirements.

Radio interferencereductionrequirements.

9ro-

REFERENCEOBY:

MIL-O-8708

MIL-O-8708

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

141L-E-7080

i41L-E-7080

MIL-E-7080

MIL-E-7080

%-umz0

zn


TABLE X. Reauired documents and corresDondina acm”licabilitvdata (continued). ,

DOCUMENT NUMBER:

MIL-F-15733

MIL-C-7762

MS33540

MIL-W-5088

MIL-R-6809(1)

MIL-B-83769(ReplacesMIL-B-6146)

AND10441(2)

OOD-C-7115

MIL-1-7032

MIL-M-8609

MIL-M-7969

MIL-G-21480(ReplacesMIL-G-6099)

DOCUMENT TITLE:

Filters and Capacitors, RadioFrequency Interference,GeneralSpecification for

Compasses, Installationof

Safety Wiring and Cotter Pinning,General Practices for

Wiring, Aerospace Vehicles

Regulator, voltage, 30 Vdc, Gen-erator, General Specificationfor

Batteries,Storage, Lead-Acid,General Specification for

Battery Installation

Converter,Aircraft, GeneralSpecificationfor

Inverter,Aircraft, GeneralSpecificationfor

Motors,General

Motors.

DC, 28V, System, Aircraft,Specification for

AC. 400 Cvcle. 115/200V.System; Aircraft,-General Specifi-cation far

Generator System, 400 Hz Ac, Air-craft, General Specificationfor

APPLICABILITY:

Any QPL itern.

Maximum compass deviations.

Safety wiring practice.

Installationrequirements.


Any QPL itern.

Entire document.

Any QPL itern.

Any QPL itern.

Requirementsand quality assurancefor DC motors.

Requirementsand quality assurancefor AC motors.

Any QPL item.for DC generators.

REFERENCEDBY:

MIL-E-7080

MIL-E-70B0

MIL-E-70B0

MIL-E-7080

MIL-E-70B0z

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080


TABLE X. fleauired documents and corresoondinciarmlicabilitv data (continued).

DOCUMENT NUMBER:

MIL-G-6162

MII--L-6723

MIL-L-6730

MIL-L-5667

MIL-L-18276

AN2552

MS25018

MIL-A-6752

MIL-V-6753

MIL-s-6i

MIL-S-3950

DOCUMENTTITLE:

Generatorand Starter GeneratorElectricDirect Current, Nominal30 Volts, Aircraft, General Spec-ificationfor

Lights,Aircraft, General Specifi-cation for

Lighting Equipment;Exterior,Air-craft (GeneralRequirementsfor)

Lighting Equipment,AircraftInstrumentPanel, General Specifi-cation for InstalIation

Lightingof Aircraft Interior,InstalIation

Receptacle,ExternalPower, 28 Vdc

Connector,Receptacle,ExternalElectricPower, Aircraft, 28 Vdc,Jet Starting

Ammeters,Voltmetersand Load-meters, Direct Current

Voltmeter,0-150 Volt, 330 to1200 Cycle, AlternatingCurrent

Shunts, Instrumental, External,50mV (Light Weight Type)

Switch, Toggle, General Specifi-cation for

APPLICABILITY:

Any QPL itern.

Any QPL item.

Exterior 1ighting equipmentinstallation.

Instrument lighting installation.

Naval aircraft 1ighting require-ments.

Entire document.

Entire document.

Any QPL itern.

Any QPL itern.


Any QPL item.

REFERENCED BY:

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080x

>~w

y:

MIL-E-7080 ~ q0XCv n

MIL-E-7080 “ ;

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-708Q

MIL-E-7080


-Jw

DOCUMENT NUMBER:

MS3505(ReplacesAN3114)

TABLE X. Reauired dacuments and corresDondina agg\icabi1itv data (continueci).

MS90362(ReplacesAN3114)

MIL-S-8834

MS33630

MIL-STD-203

MIL-STO-250

MIL-G-7703

MIL-S-8805(ReplacesMIL-S-6743 andMIL-S-6744)

MIL-S-6746(3)

MIL-S-6807

DOCUMENT TITLE:

Cover for Use With MS90362,ExternalPower Receptacle

Connector,Receptacle,ExternalElectricPower, Aircraft,115/200V, 400Hz

Switch, Toggle, Positive Break,General Specificationfor

Switch,Toggle, Installationof

Aircrew Station Controls andOisplays: Assignment,Location,and Actuationof, for Fixed MingAircraft

AircrewStation Controls and Ois-plays for Rotary Wing Aircraft

Guard, Switch, General Specifica-tion for

Switchesand Switch Assemblies,Sensitiveand Push Action (SnapAction),General Specification for

Switch, Rotary, Shielded,AircraftIgnition

Switch, Rotary, Selector Power,General Specificationfor

APPLICABILITY:

Entire document.

Entire document.

Any QPL item.

Entire document.

Orientationof switches.

Orientationof switches.

Any QPL itern.

Any QPL itern.


Any QPL item.

REFERENCEDBY:

MIL-E-7080

MIL-E-70B0

MIL-E-7080

MIL-E-7080

MIL-E-7080

HIL-E-7080

HIL-E-70B0

MIL-E-7080

MIL-E-7080

MIL-E-7080


TA8LE x. Reauired documents and corresDondina aoDlicabilitv data (continued~.

DOCUMENT NUMBER:

MIL-C-5809

MS33590

MIL-F-5372

MIL-F-15160

MIL-R-6749

u MIL-R-26a

MIL-R-6106

I MIL-C-5026

00CUMENT TITLE:

Circuit Breaker, Trip-Free,Air-craft, General Specificationfor

Circuit Breaker Installation

Fuse, Current Limiter Type, Air-craft

Fuse, Instrument,Power andTelephone

Rheostat,Aircraft Power

Resistor, Fixed, Nire-Wound(Power Type), General Specifica-tion for

Relays, Electric,Aircraft, GeneralSpecificationfor

Cutout, Relay, Engine Generator

APPLICABILITY:

Any QPL itern.

Entire document.

Any QPL item.

Any QPL item.

Any QPL itent.

Any QPL itern.

Any QPL itern.

Any QPL item.

REFERENCEDBY:

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080I

The remainingsecond tier references,tiered to MIL-E-7080,are for guidanceand information.

Third Tier

MIL-B-5087 Bonding, Electricaland Lightning Exteriorbondingand connections; MIL-F-7179Protection,for Aerospace Systems receptacleinstallation. MS33645

MIL-S-81733 Sealing and Coating Compound, Any QPL itern. MIL-F-7179Corrosion Resistant

MIL-S-8802 Sealing Compound, Temperature Any QPL itern. MIL-F-7179Resistant,Integral Fuel Tanksand Fuel Cell Cavities, HighAdhesion

>uv

z0

x


TABLE X. Reauired documents and corresDondina am] icabi1itv data (continued).

QQ-P-416

MIL-STD-105

FED-STD-595

MS20995

FED-STO-595

MIL-STD-411

MIL-C-25050

MIL-STO-203


MIL-S-83430 Sealing Compound, Integral FuelTank and Fuel Cell Cavities,IntermittentUse to 360°F

MIL-C-81774 Control Panel, Aircraft, GeneralSpecification for

CQ-B-613 Brass, Leaded and Nonleaded: FlatProducts (Plate, Bar, Sheet andStrip)

Bronze, Phosphor; Bar, Plate, Rod,Sheet, Strip, Flat Wire, andStructuraland Special Shaped

~-8-750

Sections

Plating,

Sampling

Colors

Cadmium (Electrodeposited)

Procedures and Tables

Iiire, Safety or Lock

Colors

Aircrew Station Signals

Colors, Aeronautical LightsLighting Equipment, GeneralRequirementfor

and

Aircrew Station Controls andOisplays: Assignment, Locationand Actuation of, for Fixed WingAircraft

APPLICABILITY:

Requirements.

Spacing of switches.

Requirements.

CompositionA.

Type II, Class 2.

Inspection level S-2; AQL of 1%.

Color No. 33538 and 37038.

Material requirements.

Color Nos.: 13655, 23655, 15102,25102.

Visual aircrew station signals.

REFERENCEDBY:

MIL-F-7179

MIL-STD-203

MS90298

MS90298

MS90298

MS90298

MS33645

MS33540

MS33540

MIL-L-18276

Red light requirements;white light MIL-L-18276requirements.

Lighting fixture installation; MIL-L-18276visual aircrew signals; illumina-tion:

n


TABLE X. Reauired documents and Corresvondinq aDDIicabilitvdata (continued).

um

DOCUMENT NUMBER:

MIL-STD-250

MIL-L-25467

MS25027

MIL-P-7788

AN3037-8A

MIL-P-6781

MIL-B-5087

MIL-W-5088

MIL-C-25050

MIL-L-27160

MIL-L-25467

DOCUMENT TITLE:

Aircrew Station Controls andOisplays for Rotary Hing Aircraft

Lighting, Integral, Red, AircraftInstrument,General Specificationfor

Light Assembly, Cockpit, Fixed

panels, Information,IntegrallyIlluminated

Light Assembly, Cabin Oome

Control Panel: Aircraft EquipmentRack or Console Mounted

Bonding, Electrical and LightningProtection for AerOSDaCe Vehicles

Wiring, Aerospace Vehicles

Colors, Aeronautical LightsLighting Equipment,GeneralReauirement for

and

Lighting, Instrument,Integral,White, General Specificationfor

Lighting, Integral, Red, AircraftInstrument,Genera) Specificationfor

APPLICABILITY: REFERENCE BY:

Lighting fixture installation; MIL-L-1B276visual aircrew signals; illumina-tion.

Primary lighting system; integrally MIL-L-182761ighted instruments.

Secondary instrument 1ightingsystems.

Any QPL itern.

Cockpit 1ights for emergencymain-tenance and flight.

Standard control panels forcontrol of lights.

Instrument lighting installationrequirements.

Instrument lighting installationrequirements.

MIL-L-1B276

MIL-L-18276

MIL-L-18276

MIL-L-18276

MIL-L-5667

MIL-L-5667

Red color reouirements for external MIL-L-5667lighting.

White lighting requirementsfor MIL-L-5667internal lighting.

Red 1ighting requirementsfor MIL-L-5667internal lighting.


TABLE X. Reauired documents and corresDondinq aDDlicabilitvdata (continuedl.


MIL-L-5057

MS25027

MS33568

MS33569

MS33570

MS33571

MIL-STO-838(ReplacesMIL-L-6880)

MIL-STD-195

t41L-I-6181

MIL-STO-704

MIL-A-8625

Light, Instrument, Individual,General Specification for

Light Assembly, Cockpit, Fixed

Orive, Square Mounting Flange,With Insolute Spline Pinion

Orive, Round Mounting Flange, WithInvolute Spline Pinion

Drive, Square Mounting Flange 14ithRound Shaft and Key

Orive, Round Mounting Flange WithRound Shaft and Key

.Lubricationof Hi1itary Equipment

Marking of Connections for ElectricAssemblies

InterferenceControl Requirements,Aircraft Equipment

ElectricalPower Characteristics



Past lighting requirements. MIL-L-5667

Secondary 1ighting system (flood- MIL-L-5667lights).

Entire document.

Entire document.

Entire document.

Entire document.

Requirementsand

MIL-M-8609MIL-M-7969


MIL-M-8609MIL-M-7969 R ~

++

MIL-M-B609 ~ ~MIL-M-7969 ~ ~

nquality assurance. MIL-M-8609 0 ~

MIL-M-7969

External termination of wiring. MIL-M-8609MIL-M-7969

Requirements. MIL-M-8609NIL-M-7969

Input power requirements; MIL-M-8609Category C. MIL-M-7969

Requirementsand quality assurance. MIL-M-8609MIL-M-7969


TABLE X. Reauired documents and corresDondinu aoDlicabilitvdata (continued).

DOCUMENT NUMBER:

MIL-C-5541

MIL-M-3171

W-P-41 6

MIL-STD-81O(ReplacesMIL-E-5272)

MIL-M-14

MIL-P-15035

QQ-S-571

QQ-B-613

W-B-626

MIL-STD-105

DOCUMENT TITLE:

Chemical Conversion Coatings onAluminum and Aluminum Alloys

MagnesiumAl10Y,PretreatmentandCorrosion on

Plating, Cadmium

Processes forPreventionof

(Electrodeposited)

APPLICABILITY:

Requirementsand qua

Requirementsand qua

Type I or II.

EnvironmentalTest Methods andEngineeringGuidelines

Molding Plastics and Molded PlasticParts, Thermosetting

Plastic Sheet: Laminated,Thermo-setting,Cotton-Fabric-Base,Phenolic Resin

Solder: Tin Alloy, Tin-LeadAlloy,and Lead Alloy

Erass; Leaded and Nonleaded;FlatProducts

Brass, Leaded and Nonleaded: Rod,Shapes, Forgings and Flat ProductsWith Finished Edges

Sampling Proceduresand Tables forInspectionby Attributes

ity assurance

ity assurance

Shock, Method 516; Vibration,Method 514; Humidity, Method 507;Salt Spray, Method 509; Sand andOust, Method 510; Fungus,Method50B; Explosion,Method 511.

CFI-10 or highertype.

Requirementsand

impact strength

REFERENCE BY:

MIL-M-B609MIL-M-7969




n.

quality assurance. MIL-S-61 %

Any QPL item. MIL-S-61

Brass requirements. MIL-S-61

Brass requirements. MIL-S-6’

AQL of 1.0. MIL-S-6’


TABLE X. Reauired documentsand corres~ondinq aoolicabilitv data (continued~.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLIGIBILITY: REFERENCEDBY:

MIL-STD-202

The remaining

(1) MIL-R-6809(2) AN1044I is(3) MIL-S-6746

Test Methods for Electronicand Method 301, DielectricHith- MIL-S-61ElectricalComponent Parts standingVoltage.

third tier references,tiered to MIL-E-7080,are for guidanceand information.

is cancelled with no supersedingdocument.cancelled with no supersedingdocument.is cancel1ed with no supersedingdocument.


MIL-A-8861 Airplane Strength and Rigiidity Symmetricalflight conditions, MIL-D-8708F1ight Loads unsymmetricalflight conditions, x

z spins, gust loads. 3.?a -u o:

Second and Third Tier~ z&0-

0

Al1 documentstiered to 141L-A-8861, are for guidanceand information.Xw nn ;

First Tier (18 of ?b Oocuments) v

MIL-C-7762 Compasses, Installationof Requirementsand qualityassurance.MIL-O-8708

Second Tier

NIL-STD-765 Compass, Swinging,Aircraft, Magnetic heading groundand f1ight MIL-C-7762General Requirementsfor requirements.

MIL-C-26524(1) CalibratorSet, HagneticCompass, Requirementsand qualityassurance.141L-C-7762Type A/E37T-10

The remainingsecond tier referenc~s,tiered to MIL-C-7762,are for guidanceand information.

Third Tier

Al1 third tier references,tiered to HIL-C-7762,are for guidanceand information.

(1) MIL-C-26524is cancelled with no supersedingdocument.


TABLE X. Reauired documentsand corresuondinuarmlicabilitvdata (continued~.


Fir$t Tier (19 of 9b )Documents

NIL-F-7872 Fire and Overheat klarningSystemsConditions,Aircraft Test andInstallationof

Second Tier

MIL-E-5400 ElectronicEquipment,Aerospace.General Specificationfor

MIL-STO-704 Aircraft Electric Power Character-istics

MIL-STO-411 Aircrew Station Signals

MS25Z31-313 Lamps,‘Incandescent,CenterContact, Miniature Bayonet Base(T-3-l/4Bulb)

MIL-C-Z6482 Connectors,Electric,Circular,Miniature,Quick Oisconnect

H1L-R-6106 Relay, Electric,Aerospace,General Specificationfor

APPLICABILITY:

Fire detectionsystemtests;ground and flightoperationoffire warning system.

Materialsfor fire fighting/detection;internalwiring.

Transientvoltage”shallnotresult in a false alarm:powervariation.

Fire warning signal requirements;legend-typewarning systenwith“FIRE” in red: markingof warningsystem;overheatsignalrequire-ments.

Light signallamp requirementsfor fire warning.

Any QPL itern.

Any QPL itern.

REFERENCE BY:

MIL-D-870B

MIL-F-7872

MIL-F-7872

UIL-F-7B72

HIL-F-7B72

MIL-F-7872

MIL-F-7B72


TABLE X. Reauired documents and correspondingaoDlicabilit~ data (continued)

I

DOCUMENT NUMBER: 00CUMENT TITLE:

MIL-E-7080 Electric Equipment,Aircraft,Selection and Installationof

MIL-I-8700 Installationand Test of Elec-tronic Equipment in Aircraft,General Specification for

MIL-H-5088 Wiring Aerospace Vehicle

MIL-E-25038 Hire, Electrical, High Temperatureand Fire Resistant,Aircraft

MIL-STD-81O EnvironmentalTest MethodsEngineeringGuidelines

and

MIL-I-6181 InterferenceControl RequirementsAircraft Equipment

APPLICABILITY:

Installationof electricalandelectroniccomponentsof thefire warning system.

Installationof electricalandelectroniccomponentsof thefire warning system.

Installationof fire warningsystem wiring except for wireused in fire or overheat zone.

Any QPL item.

Environmentalconditions in-cluding high and low temperature,altitude, humidity, rain,vibration, salt spray and

EMI requirements.

The remainingsecond tier reference$,tiered to MIL-F-7872,are for guidance and

Third Tier

noise.

REFERENCE 8Y:

MIi.-F-7872

MIL-F-7872

MIL-F-7872

MIL-F-7872 zDl--u.C4

:

MIL-F-7872

information.

MIL-STO-454 Standard General Requirementsfor Requirements17 and 69 for printed MIL-E-5400wiring and internal wiring.

MIL-C-25050 Colors, Aeronautical Lights and Color and brightness of warning MIL-STD-411Lighting Equipment,General signals.


wN

TABLE X. Reauired documents and corresoondinq am licabiIitv data (continued)

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY: REFERENCE BY:

MIL-M-18012 Markings for Aircrew Station Ois- Conformanceof Ietter/number. MIL-STO-411plays, Oesign, and Configuration

MIL-STO-810 EnvironmentalTest Methods and Aeronauticalexplosionproof MIL-E-7080(Replaces EngineeringGuidelines tests for electronicequipment.MIL-E-5272)

MIL-I-6051 InterferenceLimits and Methods of Limit reguirementsfor air MIL-I-6181Measurements,Electricaland vehicles:ElectronicInstalIation in Air-borne Weapons Systems andAssociatedEquipment

The remainingthird tier references,tiered to 141L-F-7872,are for guidanceand

First Tier (2o Of 9b 00CUments~

HIL-G-7940 Gages, Liquid Quantity,Gpacitor Requirementsand qualityType, Installationand Calibrationof

Second Tier

t4S20659 Terminal,Lug, Crimp Style, Copper, Entire document.Uninsulated,Class I

—

zinformation. z.~w-u

m.YZW0-

0Em

assurance. MIL-O-8708 ~ mGWI

MIL-G7940


DOCUMENT NUMBER:

MIL-W-22759/l(ReplacesMIL-W-7139)

TABLE X. R~ irddcumn n “c rr ntinuedl.

MIL-W-16878

MIL-C-17

MIL-W-5088ww

MIL-C-26482

MIL-C-26500

00CUMENT TITLE:

Wire, Electric, Fluropolymer-Insulated, TFE and TFE CoatedGlass, Silver-CoatedCopperConductor

Wire, Electrical, Insulated,General Specificationfor

Cables, Radio Frequency,Coaxial,Dual Coaxial, Twin Conductor, andTwin,Lead

Wiring, Aerospace Vehicle

Connector, Electric,Circular,Miniature, Quick Disconnect,EnvironmentResisting

Connector,General Purpose,Electrical, Miniature, Circular,Envlronment Resisting, EstablishedReliability,General Specificationfor


Requirementsfor unshielded MIL-G-7940connector cables.

Requirementsfor unshielded MIL-G-7940connector cables.

Any QPL itern. MIL-G-7940

InstalIation requirementsforelectrical accessoriesexceptfor connectors.

Any QPL itern.

Any QPL itern.

MIL-G-7940 x

MIL-G-7940


TABLE X. Reauired documents and corresDondinq aoolicabilitYdata (continued].

DOCUMENT NUMBER:

MIL-W-2275912(ReplacesMIL-W-7139)

MIL-C-815

MIL-STD-454

W-S-571

mbMIL-B-5087

MIL-STO-704

MS.29576(1)

MIL-G-26988

DOCUMENT TITLE:

Hire, Electric, F1uropolymer-Insulated,TFE and TFE CoatedGlass, Nickel Coated CopperConductor

Connector, Electrical, Circular,High Density,Quick Disconnect,EnvironmentResisting

Standard General Requirementsfor

Solder; Lead Alloy, Tin LeadAlloy, and Tin Alloy, Flux CoredRibbon and Hire, and Solid Form

Bonding, Electricaland LightningProtection,for Aerospace Vehicles

Aircraft ElectricPower Require-ments

Flange, Attachment,Molded TankFlush and Recessed, Full Molded,Circular

Gage, Liquid Quantity, CapacitorType. Transistorized,General


Requirementsfor unshieldedcables. MIL-G-7940

Any QPL tern. MIL-G-7940

Requirement5, Soldering. MIL-G-7940

Any QPL item. MIL-G-7940x

~~“.

Aircraft structurebonding. MIL-G-7940 ~ ~u ;G.

Operational power requirements. MIL-G-7940 n ~:

Entire document. MIL-B-7940

Table I. MIL-G-7490

Specification

Al1 remainingsecond tier references,tiered to MIL-G-7840, are for guidance and information.

(1) This referencehas been cancelled with no supersedingdocument.

,,


‘r,

I

TABLE X. Reauired documents and corresDondinciatIDliCabilitV data (continued).

DOCUMENT NUMBER:

Third Tier

QQ-C-502

ASTM B75

MIL-W-5086

MIL-W-22759/1, /9, /11

MIL-W-8138111, 13, 17

MIL-C-22520/24

MIL-F-14256

HIL-P-28809

@)-s-571

MIL-T-81533

DOCUMENT TITLE:

Copper Rods and Shapes and FlatProductsWith,Finished Edges(Flat Wire, Strips and Bars)

Standard Specification for Seam-less Copper Tube

Wire, Electric, PolyvinylChlorideInsulated,Copper or Copper Al10Y

Wire, Electric, FluoropolymerInsulated,Copper or Copper Al10Y

Wire, Electric, FluoropolymerInsulated,Copper or Copper Al10Y

Crimping Tools. Terminal, Hand orPower Actuated, Hire Termination

Flux, Soldering, Liquid (Rosin8ase)

Printed Hiring Assemblies

APPLICABILITY:

Class A.

General requirements,chemicalcomposition,mechanical prop-erties, non-destructivetestingand electrical resitivitysections.

Any QPL ,item.

Any QPL

Any QPL

tern.

tern.

Requirements.

Any QPL item.

Requirementsfor cleanliness.

Solder; Lead Alloy, Tin Lead Alloy, Any QPL itern.and Tin Al10Y, Flux Cored Ribbonand Wire, and Solid Form

REFERENCED BY:

MS26059

MS26059

MS26059

MS26059

MS26059

MS26059

MIL-STD-454

MIL-STO-454

MIL-STO-454

1.1.1 Trichloroethane(Methyl Non-corrosivesolvent requirements. MIL-STO-454Chloroform) Inhibited, VaporDecreasing

>-uTm

Gx

n


TABLE X. Reauired documents and corresoandina aoDiicabilitYdata (continuedl.

DOCUMENT NUMBER:

TT-I-735

O-E-760

O-T-236

MIL-STD-750

MIL-STD-1512(ReplacesMIL-STD-833)

MIL-STD-202

MIL-P-81728

141L-STD-275

MIL-P-50884

AN960

AN935

MS35338(ReplacesMS35337)

DOCUMENT TITLE:

IsopropylAlcohol

Ethyl Alcohol (Ethanol); OenaturedAlcohol; ProprietarySolvents andSpecial IndustrialSolvents

Tetrachloroethylene (Percholoroe-thylene),Technical

Test Methods for SemiconductorDevices

ElectroexplosiveSubsystems,ElectronicallyInitiated,Design,Requirementsand Test Methods

Test Methods for ElectronicandElectricalComponent Parts

Plating, Tin Lead (Electrodeposited)

Printed Hiring for ElectronicEquipment

PrintedWiring, Flexible andRigid-Flex

Hasher, Flat

Washer, Lock-Sgring

Hasher, Lock-Spring,Helical,Regular (Medium) Series


Type 111. MIL-STD-454

Type 111. MIL-STO-454

Type III. MIL-STD-454

Method 2026, Semiconductors. MIL-STD-454

Method 2003. Micreelectronics.

Method 208, other electricalparts.


Hire attachmentrequirements.

Hire attachmentrequirements.

Light or heavy series only.

Light series. temperaturenot toexceed 400”F.

Entire document, temperaturetoexceed 400”F.

MIL-STD-454

MIL-STO-454

MIL-STD-454

MIL-STD-454

W L-SlU454

FIIL-8-5087

MIL-8-5087

MIL-B-5087

n


TABLE X. Reauired documentsand corresoondina aDalicabilitv data (continuedl.


MS35340 Washer, Lock-Spring,Helical,(Replaces Regular (Heavy) SeriesMS35339)

MS25083 Jumper Assembly, ElectricalBondingand Current Return

AN735 Clamp, Loop Type Bonding

APPLICABILITY:

Entire document,exceed 400”F.

Entire document,exceed 300”F.

Entire document,plating.

The remainingthirdtier documents, tiered to MIL-G-794fl,are for

First Tier (21 of 9b Documents)z

REFERENCEDBY:

temperatureto MIL-B-5087

temperaturenot to MIL-B-5087

except for zinc MIL-B-5087


4tlIL-@-8565 Battery Storage, Aircraft,General Any QPL itern. 141L-o-a708

Specification for

Second and Third iier~

Al1 secondand third tier references,tiered to 141L-8-8565,are for guidanceand information.

First Tier (22 of 9b Documents~

MIL-A-8591 AirborneStores, SuspensionEquip- Time for arming and rearmingfor MIL-O-8708inentand Aircraft-StoreInterface ground functionaltests.(CarriagePhase), General OesignCriteria for

Second and Third Tier\

n

Al1 secondand third tier references,tiered to HIL-A-8591, are for guidanceand infofiation.


r-””-”””“-“TABLEX. !kwuired docu ents and cor esoondinaamlm r !cabilltvdata (centinued)

DOCUMENT NUMBER: DOCUMENTTITLE: APPLICABILITY: REFERENCEDBY:

1 first Tier (23 of 9b Docur@rljQ

MIL-I-8671 Installationof Droppable Stores Ease of rearming/specif\ctime MIL-O-8708and Associated Release Systems requirementfor rearming(3.8).

I 5econd and Third Tiers,

1 Al1 second and third tler references,tiered to MIL-I-8671, are for guidanceand Information.

I first Tier (24 of 9b DO~

1“ ANSI Z39.18 Scientificand Technical Reports Entire document. MIL-D-8708

Eirst Tier (25 OfG

9b Documi@Q x

m >;MIL-I-8675 Installations: Aircraft Ar~r Rearming t!,merequirements. ~~L+8708 ~7U

~&<econd and Third Tier$ 0 sSw

All secondand third tier references,tiered to MIL-I-8675,are for guidanceand informationcnly.nn :


TABLE X. R&mired d~cuments and ccmmmdm a~~lImbilitv data LmtiuiW.


first Tier (26 of 96 DO~

NAVAIRINST 13034.I Fl\ghtClearance Policies Entire NAVAIR INSTRUCTION. MII.-D-87O8

Fi Str Tier (27 of 96 Docum@Q

MIL-C-B678 Ccollng Requirementsof Power TablesI and V. MIL-O-8708PlantInstallations

and Third Tier\

Al1 second and third tier references, tiered to MIL-C-8678,are for guidance and information.

F!rst Tier (28 of 9b Documti z>?

z hiIL-O-8683 Design and Installation of Gaseousa

Requirementsand quality assurance. MIL-D-8708 ~ yOxygen Systems in Aircraft, General ZmSpecificationfor

D-J0

z%

n “First T er (29 of 95 Do~i s

:

MIL-I-8700 Installationand Test of Electronic Installationrequirements. MIL-O-870BEquipmentIn Aircraft, GeneralSpecificationfor


TABLE X. Reauired documents and corresoondinciaDDlicabilitvdata (continuedl.


Second Tier

MIL-F-7179(1) Finishes,Coatings and Sealants forthe Protectionof Aerospace WeaponSystems

MIL-B-5087(3) Bonding, Electrical,and LightningProtection,for Aerospace Systems

MIL-STO-454 StandardGeneral RequirementsforElectronicEquipment

APPLICABILITY:

Finish and coating for metals.

Non-metal and metal bondingrequirementsincludingfinishandcoating; control panel bonding;RFI requirements;installationrequirementsfor wiring, cabling,connectors;junction box require-ments; design, constructionandtests of radomes; lightningprotection.

Requirement22, Parts Selectionand Control: Requirement16,DissimilarMetals; Requirement47, Encapsulationand Embedment;Requirement62, Human Engi-neering: Requirement58, Switches;Requirement57, Relays; Require-ment 1, Safety Oesign Criteria;Requirement33, Resistors;Reauirement 10. ElectricalConnec-to~s: Requirement53, Niiveguides;RequirementB, ElectricalOverloadProtection;Requirement37, CircuitBreakers; Requirement39, Fuses;Requirement36, Accessibility;Requirement35, Reliability.

REFERENCE BY:

MIL-I-8700

MIL-I-8700

I


TABLE X. Reauired documents and correspondingaoDIicabilitY data (continuedl.

DOCUMENT NUMBER:

MIL-C-6781

MIL-P-77B8

MIL-F-25173

MIL-C-172

MIL-M-B128B(2)

MS33630

MIL-E-5400

MIL-E-7080

MIL-W-50B8(3)

00CUMENT TITLE:

Control Panel: Aircraft Equip-ment, Rack or Console Mounted

Panels, Information,IntegrallyIlluminated

Fasteners,Control Panel, Air-craft Equipment

Cases: Bases, Mounting; andMounts Vibration (for Use IiithElectronicEquipment in Aircraft)

Mounting Bases, Flexible PlasticFoam

Switch, Toggle, Installationof

ElectronicEquipment,Aerospace,General Specificationfor

ElectronicEquipment,Aircraft,Selectionand Installationof


APPLICABILITY:

Console mounted requirements(Type I)

Any QPL

Any QPL

tern.

tern.

Any QPL itern.

Requirements.


Hermeticallysealed relay require-ments for airborne electronicequipment;shock and vibrationmaximum limits.

Aircraft electricalequipmentapplicationsbelow 55,000 feet -non-hermeticsealed relays;circuit protectiondevices.

Installationrequirements;cable1ength; junction box requirements.

REFERENCE BY:

MIL-I-8700

MIL-I-8700

MIL-I-8700

MIL-I-8700

MIL-I-B700

MIL-[-8700

MIL-I-8700

MIL-I-8700

PIIL-I-8700


TABLE X. Reauired documentsand Corresllondinqa~r)licabilitv data (continued~.

wN

DOCUMENT NUMBER:

MIL-E-6051

MS21047

MS21048

MIL-A-9094

MIL-S-9129

MIL-C-?’762

MIL-F-15733

DOCUMENT TITLE:

ElectromagneticCompatibiIityRequirements,Systems

Nut, Self-Locking,Plate, Two Lug,Low Height, Steel, 125 ksi, 450SF

Nut, Self-Locking,Plate, Two Lug,Low Height, CRES, 125 ksi, 450”Fand 800”F

Arrestor, Lighting,General Spec-ificationfor, Oesign of

Static OischargerAN/ASA-3B

Compasses, Snstal1ation of

Filters, Radio Interference


Junction box functionalrequire- MIL-I-8700ments; electromagneticcompat-ibility; filter installation.

Plating requirements. MIL-I-8700

Plating requirements.

Requirementsand qualityassurance. MIL-I-8700x

-rAny QPL item. MIL-I-8700 ~ +

Maximum magneticcompassdeviations.

Any QPL itern. MIL-I-8700 G

The remainingsecond tier references,tiered to hilL-I-8700,are for guidanceand information.

(1) MIL-B-5087requirementstake precedence.(2) Except for frequenciesand amplitude of MIL-E-5400,Figure 3.(3) In the case of a discrepancy,the requirementsof the acquir!ng activityshallgovern.

Third Tier

MS25212 Control Panel, Console Type, Air- Type I panels.craft Equipment,Base Dimensions

US25213 Control Panel, Aircraft Equipment, Installationrequirements.Typical Installation

MIL-C-6781

MIL-C-6781


TABLE X. Reauired documents and corresc)ondina aDDlicabilitvdata (continuedl.

DOCUMENT NUMBER:

MIL-STO-1472

MIL-C-81774

MIL-N-5088

MIL-M-18012

MIL-K-25049

MS33742

MIL-C-26482

TT-E-489

TT-E-527

TT-E-1757

MIL-R-6J06

(j+P-416

OOCUMENT TITLE:

Human Engineering Oesign Criteriafor Military Systems, Equipmentand Facilities

Control Panel, Aircraft, GeneralRequirements for


Markings for Aircrew StationDisplays Design and Configurationof ‘

Knobs, Control, Electronic Equip-ment, General Specificationfor

Shaft, Control Knob

Connector, Electrical, CircularMiniature,Quick Disconnect,(EnvironmentalResisting)

Enamel, Alkyd, Gloss (for Exteriorand Interior Surfaces)

Enamel, Alkyd, Lusterless

Primer Coating, 2inc Chromate,Low-Moisture-Sensitivity

Relay, Electric, Aerospace,General Specification for

Plating, Cadmiurn(Electrodeposited)

APPLICABILITY:

Control requirements.

Control requirements.

External interconnectingwiringrequirements.

Arrangement, location,operationand marking of controls.

Any QPL itern.

Rotary contro’

Any QPL itern.

Any QPL itern.

shaft reauirements

Black non-reflecting.

Exterior surface finish.

Any QPL item.

Type II, Class 2.

REFERENCEDBY:

MIL-C-6781

MIL-C-67B1

MIL-C-6781

MIL-C-6781

MIL-C-6781

MIL-C-6781

MIL-C-6781

NIL-C-6781

MIL-C-6781

MIL-C-6781

MIL-E-7080

MS21047


DOCUMENT NUMBER:

AMS 2410

MIL-STD-454

TABLE x, Reauired documents and corresDondina ao9licabilitvdata (continued)..

TT-L-32(ReplacesMIL-C-6806)

MIL-STD-105

MIL-STD-202

MIL-F-81334

MIL-A-8625

DOCUMENT TITLE:

Silver Plating, Nickel Strike,High BakeStandard General RequirementsforElectronic Equipment

Lacquer,Cellulose Nitrate,Glossfor Aircraft Use

Sampling Procedures and Tablesfor Inspectionby Attributes

Test Methods for ElectricalandElectronicComponent Parts

Foam, Plastic, Flexible,OpenCell, Polyester Type Polyurethane

Anodic Coatings for Aluminum andAluminum Alloys

APPLICABILITY:

Silver plate of threaded surfacesfor 800”F only.Requirement 57, Relays.

Lacquer requirementsforrefinishing inspection.

Sampling requirementswith anAQL of 2.5.

Method 305, value of seriescapacitor; Method 303, value ofbleeder resistor;Method 112,Test conditionC, ProcedureI;Method 106, Figure 106-1;Method 101, Test conditionB;Method 110, Test conditionA;Method 107, Test conditionA;Method 204, Test conditionC;Method 205, Test conditionB;Method 211, Test conditionAand B.


Anodizing requirementsfor al10YSexcept for 3003, 5052, 6053, 6061,6063 and 7072.

REFERENCEDBY:

MS21048

MIL-E-5400

MIL-B-50B7

MIL-A-9094

MIL-A-9094

(-i

MIL-M-B128B

MIL-M-B12B8


TABLE X. Reauired documents and corresDondinq aDDlicabilitYdata (continued).

DOCUMENT NUMBER: OOCUMENT TITLE:

MIL-F-18264

MIL-S-5002

MIL-S-8516

t41L-I-i6923aW

MIL-S-23586

MIL-M-24041

MIL-I-81550

MIL-S-12285

MIL-S-15743

141L-S-83731

141L-R-28750

Finishes,Organic, Weapons Systems,Application and Control of

Surface Treatments and InorganicCoatings for Metal Surfaces ofSystems

Sealing Compound, PolysulfideRubber, Electric Connectors andElectric Systems, Chemical1yCured

InsulatingCompound, Electrical,Embedding

Sealing Compound, Electrical,Silicone Rubber, AcceleratorRequired

Molding and Potting Compound,Chemically Cured, Polyurethane

InsulatingCompound, Electrical,Embedding,Reversion, ResistantSilicone

Switch, Thermostatic

Switch, Rotary, Enclosed


Application requirementsand MIL-F-7179quality assurance.

Requirements. MIL-F-7179

Any QPL itern. MIL-STO-454

Any QPL item.

Nonreversiontype materialrequirements.

Any QPL itern.

Any QPL itern.

Any QPL itern. HIL-STD-454

Switch requirements. MIL-STO-454

Switch, Toggle, Unsealed and Sealed Any QPLToggle, General Specificationfor

Relay, Solid State, General Any QPLGeneral SDecification for

MIL-STD-454

MIL-STD-454

MIL-STO-454

MIL-STO-454

tern. MIL-STD-454

The remainingthird tier references, tiered to MIL-I-8700,are for guidance and information.


TABLE X. Reauired documentsand corresoondinaa~glicabi1itv data (continuedl.


First Tier (30 of 9b 00Cuments)

MIL-F-8785 FlyingQualities of PilotedAir-planes

Fir ATi r~ cumen

HIL-F-9490 FlightControl Systems - Design,Installationand Test of PilotedAircraft,General Specificationfor

am Second and Third Tiers

APPLICABILITY:

Classification, naturalandartificialstal1 warningrequire-ments, maximum numberfor recovery.maximumforce values.

of spinscontrol

Requirementsand qualityassurancefor automaticflight controlsystem.

All documentstiered to MIL-F-9490 are for guidancsand information.

First Tier (32 of gb Oocuments)

HIL-O-85520 Oesign and Installationof On 6oard Raquirements,“qualityOxygen GeneratingSystems in assuranceprovisions.Aircnft, General Specificationfor

Second and Third Tiers

REFERENCEOBY:

MIL-O-8708

MIL-O-870B

HIL-CM708

All secondand third tier references,tiered to !iIL-O-85520,are for guidanceand in~ormaiian.


TABLE X. Reauired documentsand COrresCIondinq a!mlicabi1itv data (cantinued}.


First Tier (33’of 9b Oocuments~

MIL-L-85762 Lighting,Aircraft, Interior Requirements,qualityassurance hiIL-O-870BNight Vision ImagingSystem provisions.(NVIS) Compatible

Second and Third tier}

Al1 second and third tier references,tiered to MIL-L-85762,are for guidanceand reference.


MIL-A-8860 Airplane Strengthand Rigidity, Maximum grossweight for taxiingGeneral Requirementsfor and take-offfor 1andbasedand

carrier-basedaircraft;maximumweights for arrestedlandings:catzpult accessoriesrequirements.

S?cond Tier

MIL-A-8863 Airplane Strengthand Rigidity, Landing and ground handlingloads.Ground Loads for Navy AcquiredAirplanes

The remainingsecond tier references,tiered to MIL-A-8860,are for guidanceand information.

Third Tier

Al1 third tier references,tiered to HIL-A-8860,are for guidanceand information.

MIL-O-8708

MIL-A-8860

n


TABLE X. Reau.ired documentsand corresoondina aoolicabilitvdata (continued~.

DOCUMENT NUM8ER: DOCUMENT TITLE: APPLICABILITY: REFERENCEDBY:


MIL-A-8863 Airplane Strength and Rigidity, Nomenclaturedefinition:critical MIL-D-B708Ground Loads for Navy Procured gross weight requirementsforAircraft catapult launchesand arrested

landingsof both carrier-andland-basedaircraft.

second Tier

MIL-A-8860 Airplane Strength and Rigidity, Oesign weights. 141L-A-8863General Requirementsfor

xMIL-STO-2066 Catapultingand ArrestingGear Horizontalcomponentsof forces. ML-A-8863 ~ ,?

Forcing Functionsfor Aircraft 0

StructuralDesignzz&D :

The remainingsecond tier references,x0

tiered to MIL-A-8863,are for guidanceand information. nn zThird Tier

Al1 third tier references,tiered to MIL-A+363, are for guidanceand information.

First Tier (36 of 96 Oocuments)

t41L-A-aa67 Airpiane StrengthGround Tests

Second Tier

MIL-A-8868 Airplane StrengthOata and Reports

and Rigidity, Structuraldynamic tests:limits tirL-o-a70afor the landinggear servicing.

and Rigidity, Loads and analysis data. UIL-A-8867


TABLE X. ~Ruirddumn and rr dat ntinuedl.


MIL-A-8870 Airplane Strength and Rigidity, Free play measurementsfor control MIL-A-8867Vibration, Flutter and Divergence surfacesand tabs.

The remainingsecond tier references,tiered to MIL-A-8867,are for guidanceand information.

Third Tier

Al1 third tier references,tiered to MIL-A-8867,are for guidanceand information.

First Tier (37 of 96 Documents~

biIL-A-8B68 Alrplane Strength and Rigidity Report requirementsfor: Struc-Data and Reports tural Oynamic F1ight Demonstra-

tion; StructuralFlightTestAnomaly and Failure:Gun FireVibrationand AeroacousticEnvironmentMeasurements;HissileVibration and AeroacousticEnvi-ronmentMeasurements;and CatapultAeroacoustic and ThermalEnviron-ment Summary.

MIL-O-870B

UCo d an nd Third Tiers

Al1 second and third tier references,tiered to MIL-A-8868,are for guidanceand information.

First Tier (38 Of9 6 Documents)

MIL-A-8870 Airplane Strength and Rigidity, Vibration and aeroacoustical MIL-D-8708Vibration, Flutter and Divergence environmentmeasurementtest

conditions;structuraldynamicflight demonstration:aero-elastic stabilityflighttestrequirements:servicelifeandfree play measurementsof controlsurfaces, tabs and vingfolds.


N00

TABLE X. Reauired documentsand corresDondinq aDDlicabilitvdata (continued.


Sm nd Tier

MIL-A-8867 AirplaneStrength and Rigidity, Test requirementsfor servicelife MIL-A-8870Ground Tests effectson control surfacesand

tabs.

The remainingsecond tier references,tiered to MIL-A-8870,are far guidanceand information.

Third Tier

Al1 third tier references,tiered to MIL-A-8870,are for guidanceand information.

First Tier (39 of 9b Oocuments) x>~

MIL-F-15160 Fuses, Instrument,Power and Any QPL item. MIL-O-8708 ~ ~Telephone z:00

Second and Third TiersXm

n(-1

z

All second and third tier references,tiered to MIL-F-15160,are for guidanceand information. 3I

First Tier (40 of 95 Ooctiments~

MIL-F-17874 fuel Systems: Aircraft,Installa- Fue\ dumping,fesd and v~nting; MIL-Q-8708tion and Test of fuelingand defuelingand fuel

transfersystem,


DOCUMENT NUMBER:

TABLE X. Reguired documents and corresDondino aDolicabilitY data (continuedl.

Second Tier

ASTM D91O(ReplacesMIL-G-5572)

MIL-J-5624

MIL-F-18802

HIL-T-6396

MIL-T-5578

MIL-T-18847

MIL-A-25896

t41L-N-5877

DOCUMENT TITLE:

Standard Specification for AviationGasolines

Turbine Fuel, Aviation, GradesJP-4 and JP-5

Fuel and Oil Lines, AircraftInstallation

Tanks, Aircraft PropulsionFluidSystem, Internal, Removable,Non-Self Sealing

Tank, Fuel, Aircraft, Self-Sealing

Tanks, Fuel, Aircraft, AuxiliaryExternal, Design and Installationof

Adapter, Pressure Fuel Servicing,Aircraft, Nominal .2-1/2InchDiameter

Nozzle, Pressure Fuel Servicing,Locking, Type D-1

APPLICABILITY:

Grades, general, material, require-ments, and test methods sections.

Requirementsand quality assurancegas turbine, ram jet and pulse jetengine aircraft only.

Requirements.

Reauirements and aualitv assurancefor integral tasks.

Requirementsand qual

Requirements and qual

Any QPL itern.

Any QPL itern.

ty assurance.

ty assurance.

REFERENCE BY:

MIL-F-17874

MIL-F-17874

MIL-F-17874

MIL-F-17874

MIL-F-17874

MIL-F-17874

t41L-F-

MIL-F-

7874

7874


TABLE X. Reauired documents and corresDondinq aDDliCabiIitv data (continued).

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY:

MIL-B-5087 Bonding, Electrical and Lightning Bonding of adapters.Protection, for Aerospace Vehicles

MIL-C-8605 Cap, Pressure Fuel Servicing Any QPL itern.

MS29514 Flange, Adapter, Locking,Pressure Entire document.Fuel Servicing

Al1 remaining second tier references,tiered to MIL-F-17874,are for guidance and

Third Tier

MIL-STD-105Ng

FED-STD-791

ASTM 03241

MIL-I-27686

MIL-I-25017

wH-T-7oo/4(ReplacesWW-T-787)

WW-T-700/6(ReplacesHILT-789)

Sampling Proceduresand Tablesfor Inspection by Attributes

Lubricants,Liquid Fuels andRelated Products: Methods ofTesting

Standard Test Method for ThermalOxidation Stability of AviationTurbine Fuels

Inhibitor,Icing, Fuel Systems

Inhibitor,Corrosion/Lubricity;mpru.ia,Fuel SG;.jb;:(Metric)

Tube, A!um!num Alloy, Drawn,Seamless

Tube, aiuminum .Aiioy,Drawn,Seamless

REFERENCED BY:

MIL-F-17874

MIL-F-I7874

MIL-F-17874

nformation.

Inspection level II; AQL of 2.5%.

Method 9601, Inspectionrequire-ments.

Procedures (thermal stabi ity)


Any QPL itern.

Aluminum al10Y tubing for pressurefuel lines.

Aluminum alloy tubing for pressurefuel lines.

MIL-J-5624 x.D~-u-00

MIL-J-5624 : ~0

G%.,n z

MIL-J-5624m

MIL-J-5624

MIL-J-5624

MIL-F-18802

MIL-F-18802


TABLE X. R uired d ument nd r~ ility”da ontinued~.


MIL-T-8606 Tubing, Steel, Corrosion Resistant CRES tubing requirements. MIL-F-18802

MIL-H-8795 Hose Assemblies, Rubber Hydraulic Flexible tubing requirements. MIL-F-18802Fuel and Oil Resistant

TT-S-1732 Sealing Compound, Pipe Joint and Antiseize compound requirements. MIL-F-li38C2Thread, Lead Free General Purpose

MIL-B-5087 Bonding,Electricaland Lightning Bonding’requirements. 141L-F-18802Protectionfor Aerospace Systems

The remainingthird tier references,tiered to liIL-F-17874,are for guidanceand information.


MIL-C-18244 Control and Stabi1izationSystems:AutomaticPiloted Aircraft,GeneralSpecificationfor

Seco nd Tier

nIL-F-8785

MIL-5T0-203 Aircrew Station Controls and Ois-plays Assignment,Location andActuationof, for Fixed HingAircraft

141L-STO-810 EnvironmentalTest Methods and(Replaces EngineeringGuidelinesH[L-E-5272)

Automatic flight controlsystem MIL-O-8708compliance.

Minimum handlingcharactersties: HIL-C-18244longitudinalor directionallateralosciIlatorymode dumping;maximum value for overpowering(3.3 and 3.4): maneuverlimitsand control forces.

Location of disengagementswitches, knobs and controls.

Environmentalserviceconditions. ,WL-C-IS244

c-l


TABLE X. Reauired documentsand corresoondinaacmlicabilitvdata (continuedl.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY: REFERENCED BY:

MIL-STD-704 Aircraft Electric Power Character- Power source conformance. MIL-C-18244istics

MIL-E-5400 ElectronicEquipment,Airborne, Design and installationof all MIL-C-18244General Specificationfor electronic equipment in control

systems; repairable/nonrepairablemadules; materials, parts,,.processes, and non-standardpartsapproval.

MIL-E-7080 Electronic Equipment,Aircraft, Design and installationof all MIL-C-1B244Selection and Installationof electronic equipment in control

systems.

The remainingsecond tier references,tiered to MIL-C-18244,are for guidanceand information.

Third Tier

MIL-C-81774 Central Panel, Aircraft, GeneralSpecification for

MIL-S-3950 Switch, Taggle, General Specifi-cation for

MIL-S-8B05 Switches and Switch Assembly,Sensitiveand Push, Snap Action,General Specificationfor

MIL-S-22B85

MIL-K-25049

MIL-M-18012

Switch, Push Button, 11luminated,General Specificationfor

Knob, Control, Equipment,Aircraft

Markings for Aircrew Statian Ois-plays Design, and Configurationof

Ease and accuracy of switch MIL-STO-203operation with operatorsglovedhand.

Any QPL itern. MIL-STD-203


Any QPL itern. MIL-STC-203


Marking of controls, switches MIL-STO-203and knobs.

xr-l


TABLEX. Reauired documentsand corresnondinq aoolicabilitv data (continued~.

00CUMENT NUMBER: 00CUMENTTITLE: APPLICAL31LITY: REFERENCE BY:

MIL-STO-454 StandardGeneral Requirementsfor Requirements22, 28, 42, 58 and MIL-E-5400ElectronicEquipment 72 for parts selection,controls,

tuningdials, switches,and partssubstitution.

ML-C-6781 ControlPanel, Aircraft Equipment, Control panel conformance. MIL-E-5400Rack or Console Mounted

I4IL-STO-81O EnvironmentalTest Methodsand Aeronauticalexplosionproof HIL-E-7080(Replaces EngineeringGuidelines tests for electronicequipment.MIL-E-5Z72)

The remainingthirdtier references,tiered to MIL-C-18244,are for guidanceand information.0m First Tier (42 Of 9b Oocumentsl

HIL-L-18Z76 Lighting,Aircraft Intsrior,Installationof

Se ?ond Tier

HIL-STC!-411 AircrewStation Signals

MIL-C-25050 Colors,AeronauticalLightsandLfghtfngEquipment,Genera[Requirementfor

HIL-STO-Z03 Aircrew Station Controls andOisplays: Assignment, Locationand Actuation of, for F\xedHingAircraft

HIL-STO-Z50 Aircrew Station Cmtrols and

Ofsplays for Rotary Hing AircraftIlluminated

Require!nentsand qIJalit“ asSurance MIL-o-a70aof interiorand sxtsriorlightingsyst2ms.

Visual aircrew stationsignals. ML-L-18276

Red light requirements:nhite MIL-L-18276[ight requirements.

Lighting fixture installation; HIL-L-18276visual aircrew signals:.iliu-❑ination.

Lighting fixture installation: ML-L-18276visual aircrew signais;illu-mination.


TABLE X. Reauired documents and corresDondina aDDlicabilitvdata (continued).


MIL-L-25467 Lighting, Integral,Red, Aircraft Primary lighting system; MIL-L-18276Instrument,General Specification integrally lighted instruments.for

MS25027 Light Assembly, Cockpit, Fixed ~~:~;~ry instrument1ighting MIL-L-18276

MIL-P-7788 Panels, Information,Integrally Any QPL item. MIL-L-18276

AN3037-8A Light Assembly, Cabin Dome Cockpit 1ights for emergency MIL-L-1B276maintenance and f]ight.

MIL-P-6781 Control Panel: Aircraft Equipment Standard control panels for MIL-L-18276 xRack or Console Mounted control of lights: BP:&

Al1 remaining second tier references,tiered to MIL-L-18276, are for guidance and information.tiZ&“4=0

Third Tier x :.n G

MIL-STD-l333 Aircrew Station Geometry for Design eye position. MIL-STD-411 w

Mi1itary Aircraft

MIL-S-38039 Systems, 11luminated,Warning, Signal assembly requirements. MIL-STD-411Caution and Advisory, GeneralSpecificationfor

MIL-STD-783 Legends for Use in Aircrew Stations Legend presentationfor signal MIL-STD-411and on Airborne Systems lights if different from Tables

I, II and III.

MIL-C-25050 Color, AeronauticalLights and Color requirementsLighting Equipment,General for brightness.Requirementsfor

and testing MIL-STD-411


DOCUMENT NUMBER:

MIL-M-18012

TABLE X. Reauired documents and corresgondinc!aDD licabilit~data (continued).

MIL-P-21563

MIL-L-27160

MIL-L-25467

National Bureauof Standards3215

MIL-C-14806

MS27569

MS27570-B515AS15

MS27571-6809AS15

MS25237-32BAS1O

DOCUMENT

MarkingsDisplaysof

TITLE:

for Aircrew StationDesign and Configuration

Paint System, Fluorescent,forAircraft Application

Lighting, Instrument,Integral,klhite, General SDecification for

Lighting, Integral,Instrument,Generalfor

Colors

Red, AircraftSpecification

Coating, Reflection Reducing, forInstrument Cover Glass andLighting Wedges

Lamp, Incandescent,MiniatureIntegral Lighting T-1-3/4 Size

Lamp, Incandescent,MiniatureIntegral Lighting T-1-l/4 Size

Lamp, Incandescent,MiniatureIntegral Lighting T-1 Size

Lamp, Incandescent,Single ContactMidget Flanged Base (T-1-3/4Bulb)

APPLICABILITY:

Signal letteringconformance.

Any QPL itern.

and number

White illuminated.

Red i1luminated.

Light transmissionrequirements.

Reflection reducing coating forinstrumentcover glass and othertransparentelements.

Lamps”for use when helium isused in the filling medium of thehermeticallysealed instrument.

Lamps for use when helium isused in the filling medium of thehermetically sealed instrument.

Lamps for use when helium isused in the filling medium of thehermeticallysealed instrument.

Lamps for use when helium is notused or is a non-hermeticallysealed case is used.

REFERENCE BY:

MIL-STD-411

MIL-STD-411

MIL-STO-41I

MIL-STD-411

~> i=

MIL-C-25050 ~ ~MIL-L-25467 ~ +

.0Xcu

n

MIL-L-25467 “ ~m

MIL-L-25467

MIL-L-25467

MIL-L-25467

MIL-L-25467


TABLE X. Reauired documents and corresDondina aDDliability data (continued.


MS24367-715AS15

MS24515-718AS15

MIL-C-25050

MIL-C-81774~m

MIL-L-27160

MIL-L-85762

MIL-L-6723

MIL-P-77B8

MIL-L-21095

Lamp, Incandescent,MiniatureIntegral Lighting

Lamp, Sub-Miniature

Colors, Aeronautical Lights andLighting Equipment,GeneralRequirementsfor

Control Panel, Aircraft, GeneralRequirementsfor

Lighting, Instrument,Integral,14hite, General Specification for

Light, Aircraft, General Spec-ification for

Panels, Information,Integrally11luminated

Liaht. Aircraft. Emeraency(I;ertiaActuated, fo; Fi~edWing Aircraft)

Al1 remainingthird tier references,tiered to

APPLICABILITY:

Lamps for use when helium is notused or is a non-hermeticalIysealed case is used.

Lamps for use when helium is notused or is a non-hermeticallysealed case is used.

All light must meet aviationredrequirements.

Brightnessrange for knobpositions and instrumentfacelettering.

Cover glass color, white, withoutIamp.

Cover glass color, anvis green,8A,,.

Any QPL item.

Any QPL item.

Emergency exit lighting.

MIL-L-18276,are for guidance and

REFERENCE BY:

MIL-L-25467

MIL-L-25467

MIL-L-25467

MIL-L-25467Pv

,%z

MS25027 0%o

MS25027

MS25027AN3037

MIL-C-6781

MIL-C-67B1

information.


lALILL~. Mulrea aocumnls ana corresDonalna aoDllcaDlIItv aata <conrlnueal.

DOCUMENT NUMBER: 00CUMENT TITLE: APPLICABILITY:

Fi Str Tier (43 of 96 Oocuments)

MIL-H-18325 Heating and Ventilating Systems, Carbon monoxide, fuel vaporAircraft: General Specification concentration,and other irritablefor contaminant limits requirements.

Second Tiec

MIL-C-)8591(1) Carbon Monoxide, Elimination, Lower explosive Iimit of theRequirements for mixture for gases contaminated

with carbon monoxide.

MIL-I-8670 Installationof Fixed Guns and Fixed gun “installationgun gasAssociated Equipment in Naval elimination.Aircraft

:w MIL-I-8673(2) Installationand Test of Aircraft Flexible weapons system gun gas

Flexible Weapons Systems elimination.

All rema!ning second tier references, tiered to MIL-H-18325, are for guidance and information

REFERENCE BY:

MIL-O-8708

MIL-H-18325

MIL-H-18325 z

(1) This document has been canceled and superseded by MIL-STD-800, which has been canceled with nosupersedingdocument.

(2) MIL-I-8673 is canceled with no superseding document.

Third Tier

AlI third tier references, tiered to MIL-H-18325, are for guidance and information.

First Tier (44 of 96 00~

MIL-S-18471 System, Aircrew Automated Escape, Ejection clearances, design and MIL-O-8708Ejection Seat Type, General Spec- placement of escape system cod-ificationfor trols, manual egress and under-

water ejection escape performance,automated escape.


TABLE X. Reauired documents and corresDondinq acmlicabilitY data (continued)

DOCUMENT NUMBER:

Second Tier

MIL-STD-1472

MIL-C-7905

MIL-S-B1018

MIL-C-7958wz

MIL-STD-l333

MIL-M-8650

DOCUMENT T’TLE:

Human EngineeringDesign

Cylinder, Compressed Gas, Non-Shatterable

Survival Kit Container, AircraftSeat, With Oxygen, GeneralSpecificationfor

Control, Push-Pull,Flexible andRigid

Aircrew Station Geometry forMilitary Aircraft

Mockups, Aircraft, General Spec-ification for

APPLICAB1 ITY:

Escape system control placement.

Any QPL item.

Any QPL

Any QPL

tern.

tern.

Ejection clearances.

Ejection clearance mock-up.

REFERENCED BY:

MIL-S-18471

MIL-S-18471

MIL-S-18471

MIL-S-18471

MIL-S-18471

MIL-S-18471r)

All remaining second tier references,tiered to

Third Tier

MIL-S-18471, are for guidance and information.

MIL-A-23121 Aircrew Environmental, Escape and Escape capsule requirements. MIL-STD-1472Survival Cockpit Capsule System;General Specification for

MIL-M-8650/2 Aircrew Systems, Mockup Inspection Mockup requirements. MIL-M-8650.Check-Off List

Al1 remainingthird tier references,tiered to MIL-S-18471, are for guidance and information.

——


TABLE X. Reauired documents and corresDondina aDDlicabi1itv data (continued~.

DOCUMENTNUMBER: 00CUMENT TITLE: APPLICABILITY: REFERENCE BY:

FirstTier (45 of 9b OOCUments]

MIL-T-18606 Test Proceduresfor Aircraft Measurementof temperatures; MIL-O-8708EnvironmentalSystems test procedures (requirements

and quallty assurance)forcockpit and cabin pressurizing,air conditioningand defoggingsystems and for cockpitandcabin nonpressurizingheating,ventilatingsystems.

Seco nd Tier

N t41L-T-5842 Transpar~t Areas on Aircraft Oesign atunsphericSurfaces (Windshieldsand for flight testingCanopiSS), Rain Removingand systems.Washing Systems forDefogging,Oeicing,Specificationfor

The remainingsecondtler references.

Third Tier

Oef;osting, -General

conditionsof defogging

tiered to HIL-T-18606,are for guidanceand information.

MIL-STD-21O Climatic Informationto Determine Ambient atmosphereconditions. MIL-T-5842Design and Test RequirementsforMllitary Systemsand Equipment

The remainingthird tier references,tieredto MIL-T-18606, are for guidanceand information.


TABLE X. Reuuired documentsand corresgondina aoplicabilitv data (continuedl.

00CUMENTNUMBER: 00CIJMENTTITLE:

First Tier (46 of 96 oocuments~

MIL-T-18607

Seco nd Tier

AN9500(1)

MIL-H-5484

14S28741(ReglacesAH5264)

Wl+-T-700/4(ReplacesNJ4-T-787)

MIL44-5088

“MIL-B-5087

MIL-STO-81O(ReplacesMIL-E-5272)

Thermal Anti-IcingEquipment,Wing and Empennage

Engines: General SpecificationforAircraft, Reciprocating

Heater, Aircraft,CombustionType

Hose Assembly, DetachableEndFitting,Medium Pressure

Tube, Aluminum Alloy, Orawn,Seamless

Wiring, AerospaceVehicle

Bonding, Electrical,and LightningProtection,for AerospaceSystems

EnvironmentalTest MethodsandEngineeringGuidelines

APPLICABILITY:

Thermal anti-icingsystemdesign,installation and performance.

Exhaust back pressurerequire-ments with heat exchangersinstalled.

Combustion heater requirements.

Hose assembly fuel ‘line.

REFERENCE BY:

MIL-O-8708

MIL-T- B507

MIL-T-18607x

t41L-T-l8607 ~ ~-OFm2ZZa

0Z9Requirementsand qualityassurance. t41L-T-lB607 ~ m

::

Electrical system installation. HIL-T-18607

Electrical bondingwith emphasis MIL-T.-1B6O7on thermal expansionprovisions.

Required environmentaltests. MIL-T-18607


TABLE X. Reauired documents and corresoondina aDDlicabilitydata (continuedl.


MIL-C-5015 Connector, Electrical,Circular Any QPL itern. MIL-T-18607Threaded, AN Type, General Spec-ification for

MIL-E-7080 Electric Equipment,Aircraft, Installationof electrical MIL-T-18607Selection and Installationof systems.

The remaining second tier references,tiered to MIL-T-18607, are for guidanceand information.

(1) AN9500 is canceled with no supersedingdocument.

Third Tier

NMIL-H-8795w Hose Assembly, Rubber, Hydraulic

Fuel and Oil Resistant

t4S25274 Cap, Electrical (Wire End, CrimpStyle, Type II, Class 1)

MIL-E-6051 ElectromagneticCompatibiIityRequirements,System

MIL-C-7762 Compass, Installationof

MIL-L-6806 Lacquer, Clear, Aluminum CladAluminum Alloy Surfaces

MIL-STO-81O EnvironmentalTest Methods and(Replaces EngineeringGuidelinesMIL-E-5272)

MS90298 Connector, Receptacle,ElectricConnector

Use, operating pressureand agecontrol of hose assembly.

Cap for undesignatedwire end.

Routing of wiring, includingRFand antenna cables,to minimizeelectromagneticInterference.

Maximum allowablecompassdeviation.

Clear lacquer to be used foreasier future bondingInspections.

Explosive proof tests.

Fuel nozzle groundingreceptacles.

n ;

MIL-W-5088 :

MIL-W-5088

MIL-B-5087

MIL-E-70B0

MIL-E-7080


TABLE X. Reauired documents and corresDondinq agDlicabilitv data (continuedl.

DOCUMENT NUMBER:

MS33645(ReplacesANDI0439)

MIL-B-5087

MIL-E-6051

MIL-I-61131

MIL-F-15733

MIL-C-7762

MS33540

tiIL-w-5088

AND10441(2)

MS33630

MS33590

fX?-S-763

DOCUMENT TITLE:

Receptacle,Grounding, Installationof

Bonding, Electrical,and LightningProtection,for Aerospace Systems

ElectromagneticCompatibi1ityRequirements,System

InterferenceControl Requirements,Aircraft Equipment

Filters and Capacitors, RadioFrequency Interference,GeneralSpecificationfor

Compass, Installationof

Safety Wiring and Cotter Pinning,General Practicesfor

Wiring Aerospace Vehicle

Battery Installation

Switch, Toggle, Installationof

Circuit Breaker Instailation

Steel 8ar Wire, Shape and Forgings,Corrosion Resisting

APPLICABILITY:

Fuel nozzle installation.

Electrical bonding.

Electrical equipment installationconformance.

Radio interferencereduction.

Any QPL itern.

Maximum requirementsfor compassdeviations.

Safety wiring practice.

Installationof wires.

Battery installationrequirements


Entire document.

Class 321.

REFERENCE BY:

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-7080

MIL-E-70B0

MIL-E-7080

MIL-E-70B0

MIL-H-5484


TABLE X. R uir urnn~. licabili cent nu

DOCUMENT NUMBER :

MIL-STO-810(Replaces)MIL-E-5272)

MIL-STD-704

MIL-I-6181

N MIL-C-5015

m

MIL-A-8625

W-P-416

MIL-G-5512

MIL-J-5624

MIL-H-18325

DOCUMENT TITLE : APPLICABILITY:

Environmental Test Methods Method 514 (Vibration); Method 511and Engineering Guidelines (Explosion); Method 507 (Humidity);

Method 508 (Fungus); Method 509(Salt Spray) and Method 510 (Sandand Dust).

Aircraft Electric Power Category B.Characteristics

Interference Control RequirementsAircraft Equipment

Connectors, Electrical , CircularThreaded, General Specification for

Anodic Coatings for Aluminum andAluminum .Alloys


Gasoline, Aviation, Grades 80)87,.100/130, 115/145

Jet Fuel, Grades JP-4 and JP-5

Heating and Ventilating Systems,Aircraft: General %ecification

Radio interference requirements.

Any QPL item.

Anodizing requirements for aluminumparts except for electricalreceptacles.

Requirements.

Grade 115/145.

Grade JP-4/JP-5.

Flight testing requirements.

for

(2) AND10441 has been canceled with no superseding document.

REFERENCED BY:

MIL-H-5484

MIL-H-5484

MIL-H-5484

MIL-H-5484 xPF-u y~

MIL-H-5484 ~ax znr-l GWY

MIL-H-5484

MIL-H-5484

MIL-H-5484

MIL-H-5484

The remaining third tier references, tiered to MIL-T-18607, are for guidance and information.


TABLE X. Reauired documents and corresoondinq acmlicabilitv data (continuedl.

DOCUMENT NUMBER: OKLIMENT TITLE:


MIL-E-18927

Second Tier

MIL-STD-21O

N H~L-S~54m

WL-7-23103

MIL-E-7080

MIL-STD-800(1)

MS16052

MS33561

MS33562

Environmental Control Systems,Aircraft, General Specificationfor

Cl,imatic Information to DetermineDesign and Test Requirements forMilitary Systems

Standard General Requirements forElectronic Equipment

Thermal Performance Evaluation,Airborne Electronic Equipment andSystems, General Requirements for

Electronic Equipment, Aircraft,Selection and Installation of

Procedure for Carbon tlonoxideDetection and Control in Aircraft

Air Inlet, Combat Aircraft, GroundCooling

Connection, Aircraft Ground AirConditioning, 5 Inch, MinimumRequirements

Connection, Aircraft Ground AirConditioning, 8 Inch, MinimumRequirements


Requirements for”carbon monoxide MIL-D-8708contamination; aircraft pressuri-zation: defogging; adequatecooling under all conditions.

Ambient atmospheric conditions. MIL-E-18927

z

Requirement 52, Thermal Design. MIL-E-18927 ~ ~~w

Steady state thermal performance MIL-E-189271imit for cooled avionic equipment.

,.,zox(-)

Electrical equipment coolingrequirements.

Maximum allowable carbon monoxidelimits.

Entire document.

Entire document.

Entire document.

MIL-E-18927

MIL-E-18927

MIL-E-18927

MIL-E-18927

MIL-E-18927


TABLE X. Reauired documents and corresoondina ilDDlicabilitv data (continued).

DOCUMENT NUMBER: DOCUMENT TITLE : APPLICABILITY: REFERENCED BY:

MIL-T-18606 Test Procedures for Aircraft Cabin Requirements and quality assurance. MIL-E-18927Pressurizing and Air ConditioningSystems

(1) MIL-STD-800 has been canceled with no superseding document.

All remaining second tier references, tiered to MIL-E-18927, are for guidance and information.

Third Tier

MIL-T-5842

MIL-STD-21O(ReplacesANA BULL 421)

F-F-300

MIL-F-16552

MIL-B-23071

Transparent Areas on AircraftSurfaces (Windshields andCanopies): Rain Removing andWashing Systems for, Defrosting,Deicing, Defogging, GeneralSpecification for

Climatic Information toDesign Requirements forSystems and Equipment

DetermineMilitary

Filter; Air Conditioning: ViscousImpingement and Ory Types, Clean-able

Filter, Air Environmental ControlSystem, Cleanable Impingement(High Velocity Type)

Blower. Miniature for Coolins.Electric Equipment, General -”Specification for

Defogging system testing. MIL-T-18606

n? As 24Critical design temperatures for

202MIL-T-18606 ~ n

air conditioning. zVI

Requirements and quality assurance. MIL-STD-454

Any QPL item. MIL-STO-454


The remaining third tier references, tiered to MIL-E-18927, are for guidance and information.


TABLE X. Reauired dacuments and carresaondinq aDDlicabilitv data (continued~.



MIL-D-19326 Design and Installation of LiquidOxygen Systems in Aircraft, GeneralSDecification for

Sec ond Tier

MIL-C-25969

MIL-A-23121

Nz

MIL-O-27335

MIL-S-81018

MIL-1-81387

MIL-I-25645

MIL-I-81388

FIIL-C-198D3

Capsule, Emergency Escape Systems,General Specification for

Aircrew Environmental Escape andSurvival Cockpit Capsule System;General Specification for

Oxygen System. Survival Containerand Oxygen Kit, General Spec for

Survival Kit Container, AircraftSeat, With Oxygen, General Spec-ification for

Indicator, Liquid Oxygen Quantity

Indicator, Liquid Oxygen Quantity,Capacitance Type, General Spec for

Indicator, Repeaters, LiquidOxygen Quantity

Converter, Liquid Oxygen, 10L,GCU-24A

APPLICABILITY: REFERENCED 8Y:

Requirements and qua]ity assurance. MIL-D-8708

Any QPL item.

Pressurization andcapsule systems.

oxygen far

Seat or pan back pack emergencyoxygen system requirements.

Any QPL item.

Any QPL 1tern.

Requirements.

Any QPL item.

Any QPL item.

MIL-D-19326

MIL-D-19326

HIL-D-19326

MIL-D-19326

HIL-&l 9326

MIL-D-19326

n

MIL-O-19326

MIL-D-19326


DOCUMENT NUMBER:

MIL-C-19328

MIL-C-25666

MS90341

TABLE X. Re ir d umen s and~ licabilitv da ntinued~.

MIL-D-26392

MIL-O-26393

MIL-S-8B05/3

MIL-R-2541O

MIL-W-5088

MIL-E-5400

MIL-R-83178

MIL-STD-203

00CUMENT TITLE:

Converter, LiquidMBA-5A

APPLICABILITY:

Oxygen, 5L, Any QPL item.

Requirements.

Mounting Bracket,Mating Portion for 5 and 10

Configuration, Converter bracket configuration.

Liter-Oxygen Converters

Dummy Converter, Liquid Oxygen Requirements.Indicator System, 10 Liter, CRU-23/A

OunmIyConverter, Liquid Oxygen Requirements.Indicator System, 25 Liter, CRU-24/A

Sw~tch, Push, 10 A~peres and LOW Any QPL itern.Level, Ousttight

Regulators, Oxygen, Oiluter-Demand, Requirements automatic diAutomatic Pressure-Breathing and oxygen regulator.

Wiring, Aerospace Vehicle External wiring.

Electronic Equipment, Aerospace, Cabling and connectors.General Specification for

Regulator, Oxygen, Oiluter-Oemand, Any QPL itern.Automat ic-Pressure-Breathing,General Specification for

Aircrew Station Controls and Location of panel mountedOisplays Assignment, Location, regulator.and Actuation of, for Fixed WingAircraft

uter

REFERENCE BY:

MIL-D-19326

MIL-D-19326

MIL-O-19326

MIL-D-19326

MIL-O-19326 x>~m

y~MIL-O-19326 ~ ~

0z=

0;MIL-O-19326

:

MIL-D-19326

MIL-D-19326

MIL-D-19326

MIL-O- 9326


~..

TABLE X. Reauired documents and corresoondina aoolicabi1itY data (continuedl.

DOCUMENT NUMBER :

MIL-V-9050

MS22068(-1, -2, -7, -8)

MIL-V-25962

MS33656

AN929-5

MIL-V-25513

MIL-V-790B

MIL-H-22343

MIL-H-26626

AMS 4071

MIL-T-8506

ANO 10104

OOCUMENT TITLE:

Valves, Oxygen, Pressure Relief,Aircraft

Coupling Assemblies, Quick Dis-connect Aircraft Liquid OxygenSystems

Fitting End, Standard Dimensionsfor Flared Tube Connection andGasket Seal

Cap Assembly, Pressure Seal FlaredTube Fitting

Cap Assembly, Pressure Seal ,Flared, Tube Fitting

Valve, Check, for 300 PSI LiquidOxygen Converter System, Type MH-1

Valves, Check, Aircraft LowPressure Oxygen Systems

Hose Assemblies, Metal , LiquidOxygen

Hose Assembly Non-MetallicTetraf1uoroethylene, Oxygen

Aluminum Alloy Tubing, Hydraulic,Seamless, Drawn, Round 2-5Mg-O.25Cr (5052-0) Annealed

Tubing, Steel, Corrosion Resistant(304) Annealed, Seamless and Welded

APPLICABILITY:

Any QPL itern.

Requirements.

Requirements for use with apermanently installed converter.

Requirements.

Cap with chain for use over thedrain valve.

Requirements for use with morethan one installed converter.

Requirements.

Requirements to -65”C.

Requirements for flexibility to-65”C.

Aluminum alloy tubing.

Requirements for 304 steel.

Tubing, Steel, Corrosion-Resistant, Requirements.Round, Standard Dimensions for

REFERENCE BY:

MIL-O-19326

MIL-O-19326

MIL-D-19326

MIL-D-19326z

G

MIL-O-19326

MIL-O-19326

MIL-D-19326

MIL-D-19326

MIL-D-19326

MIL-O-19326


i

TABLE X. Reauired documents and corresDondina amslicabi1itv data (continued),

DOCUMENT NUMBER:

MIL-B-5087

MS33583

MS33584

MS33611

44A25450

MIL-T-27730

MIL-H-B1581/5

MS22059

MS22061

60D3570

53C3794

53D3970

DOCUMENT TITLE:

Bonding, Electrical and LightningProtection, for Aerospace Systems

Tubing End, Double Flare, StandardDimensions for

Tubing End, Standard Dimensions forFlared

Tubing, Bend Radii

Sleeve, Oxygen Coupling

Tape, Antiseize,Tetrafluoroethylene, with Dispenser

Hose Assemblies, Breathing Oxygen,Low Pressure, Connector toRegulator

~;n System, Portable, 250.! High Pressure Aircraft

oxygen System, Portable, 96Cu In.; High Pressure Aircraft

Cylinder and Regulator, BreathingOxygen, Portable A/U26S-3,Assembly of

Cylinder and Regulator, BreathingOxygen, Portable

Mask-Cylinder-Regulator, Oxygen,Portable, Aircraft, Firefighters


Requirement for tube bonding. MIL-O-19326

Requirements. MIL-D-19326

Requirements. MIL-D-19326

Maximum bend radius. MIL-D-19326

Requirements, oxygen coupling. MIL-D-19326z

Requirements and quality assurance. MIL-D-19326 ~ ~T?

Any QPL itern.

Requirements.

Requirements.

Requirements w/o refi’

Requirements with refi

Requirements with refi

Iing.

MIL-O-19326

MIL-D-19326

MIL-D-1 9326

ing.

ing.

MIL-D-19326

MIL-D-19326


TABLE X. Reauired documents and corres!Jondina aDDliCabilitY data (continued).


Requirements.

Requirements for valve end clip.

Requirements.

Lubricant reauirements.

Type I and II.

MIL-D-19326

MIL-D-I9326

MIL-D-19326

MIL-D-19326

MIL-D-19326

Requirements and quality assurance.

DOCUMENT NUMBER : DOCUMENT TITLE:

MS22032 Recharger Assembly, Portable Oxygen

46A16236 Clip, Recharger LeviPressureOxygen System

MIL-T-81553 Regulator, Chest Mounted, 100Percent Oxygen, Positive Pressure,CRU-79/P

MIL-G-27617 Grease, Aircraft and Instrument,Fuel and Oxidizer Resistant

MIL-O-2721O Oxygen, Aviator’s Breathing,Liquid and Gas

MIL-T-38170 Tank, Mobile Storage, LiquidOxygen, TMU-27/M

MIL-T-26069 Trailer, Compressed Gas Cylinder,AF-M32R-3, High Pressure, 2 14heel6 Cylinder Capacity

MIL-L-25567 Leak Detection Compound,Oxygen Systems

The remaining second tier references, tiered to MIL-D-19326, are for guidance and information.

Jhird Tier

AMS 5512 Steel Sheet, Strip and Plate,Corrosion and Heat Resistant

141L-STO-454 Standard General RequirementsElectronic Equipment


Leak test compound; Ieakagerequirements.

MIL-D-19326

MIL-D-19326

MIL-D-19326

Corrosion and heat resistant steel. MS90341

for Requirement 10, Electrical MIL-E-5400Connectors: Requirement 65. Cable,Multiconnector.


NNw

DOCUMENT NUMBER :

ASA B46

W-S-698

TABLE X. uir o umen an r~ It ill ntinued~.

ASTM ,4853(ReplacesQQ-W-461 )

ASTM A818(Replaces~!4-461 )

ASTM A641(ReplacesQQ-W-461)

ASTM A809(ReplacesQ+W-461 )

Q&S-766

MIL-T-5561

V-T-295

N-B-626

DOCUMENT TITLE:

Balancing Flexible Rotors,Procedures for

Steel Sheet and Strip, Low Carbon

Standard Specification for Wire,Carbon, for General Use

Wire, Carbon Steel , Coppered

Standard Specification for Zinc-Coated (Galvanized) Carbon SteelWire

Wire, Carbon Steel , AluminumCoated (Aluminized)

Steel Plates, Sheets and Strip,Corrosion Resisting

Tape and Webbing, TextiIe, WovenReinforcing, Cotton

Thread, Nylon

8rass, Leaded and Nonleaded: Rod,Shapes, Forgings and Flat ProductsHith Finished Edges (Bar and Strip)

APPLICABILITY:

Flare sealing surface (RHR).

No. 3 temper steel (1/4 hard)

Procedures and calculationssection.

Procedures and calculations.



Requirements for CRES strip.

Type II.

Size E, Type II, Class 1 or 2

Composition 360 or 377.

REFERENCED BY:

MS33583

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059MS22061

D-u-umz0

xr)


DOCUMENT NUMBER :

TT-P-1757

TT-E-516

FED-STD-595

QQ-P-416

QQ-B-654

MIL-H-6875

MS33584

(&P-35

ASTM E8(ReplacesFED-STD-151 ,Method 211)

MS21211

TABLE X. Reauired documents and corresoondina aoDlicabi lit~ data (continued~.

DOCUMENT TITLE: APPLICABILITY:

Primer Coating, Zinc Chromate, Low Finish requirements.Moisture Sensitivity

Enamel, Lusterless, Quick Drying, Any QPL item.Styrenated Alkyd Type

Colors Color 37038.

Plating, Cadmium (Electrodeposited) Type I, Class 1.

Brazing Alloys, Silver Class BAg-5.

“

Heat Treatment of Steel , Process Temperature control requirements.for

Tubing End, Standard Dimensions Minimum dimensional requirements.for Flared

Passivation Treatments for Cor- Requirements.rosion Resisting Steel

Metallic Materials, Tension Procedures and calculations.Testing of

Valves, Check, Aircraft, Low Entire.document.Pressure Oxygen

REFERENCE BY:

MS22059MS2206I

MS22059MS22061

MS22059MS22061

MS22059MS22061

MS22059 zDr

MS22061 w &!%1

MIL-T-8506 % ~gEc-ln

MIL-T-8506zW

MIL-T-8506

MIL-T-8506

MIL-V-7908


TABLE X. ir omnanrr~ 1 ilttv d nti uedl.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILIN: REFERENCED BY:I

MIL-T-27730 Tape, Antiseize, Polytetrafluoroe- Requirements and quality assurance. MIL-V-79O8. . . . . . .tnylene NlttsLnspenser

MIL-C-81302 Cleaning Compound, Solvent, Requirements and qualTrichlorotri fluroethane

MIL-C-81533 Trichloroethane, 1,1,1 (Methyl Requirements and qualChloroform) Inhibited, VaporDecreasing

ty assurance. MIL-V-790B

ty assurance. MIL-V-7908

I MIL-A-8625 Anodic Coatings for Aluminum and Requirements and aualitv assurance. MIL-V-7908

I Aluminum Al10YS. .

xN

IN

.m MIL-C-81590 Cockpit Canopy System, Fixed Wing Transparency construction design. MIL-A-23121 ~ ~

Single and Multlplace, Fighter mz&iAircraft and Trainer Aircraft. 0.2

X- 0n s

nformation. w-l

General Specification for

The remaining third tier references, tiered to MIL-D-19326, are for guidance and


TABLE X. Reauired documents and corresDondina aDolicabilitv data (continued~.


First Tier ‘(49of 9b DocumentQ

wNm

MIL-A-19736

Second Tier

tlIL-F-7179

MIL-A-8625

(jQ-P-416

QJ-C-329

t’lIL-H-8775

MIL-STD-2175(Replaces141L-C-6021)

MIL-T-5624

MS29513

Air refuelingSpeciftcation

Systems, Generalfor

Finishes, coatings, and Sealantsfor the Protection of AerospaceWeapons Systems



chromium Plating, Ei~ctrodeposited

Hydraulic System Components, Air-craft and Hissiles, General Spec-ification for

Castings, Classification andInspection of

Turbine Fuel, Aviation Grades JP-4,JP-5, and JP-5/JP-8 ST

Packing, Preformed, HydrocarbonFuel Resistant, “O” Ring

APPLICABILITY:


Requirements and qua]ity assurancefor finishes.


Non-working steel surfaces andCRES .

Class 2.

Hydraulic system finish.”

Class IB.

Fuel requirements;JP-4 and JP-5.

Dimensional requirementsonly.

REFERENCED BY:

MIL-D-8708

MIL-A-19736

MIL-A-19736x

>.MIL-A-19736 -

MIL-A-19736

MIL-A-19736

MIL-A-19736


TABLE X. Reauired documents and corresoondina apolicabi1it~ data (contlnued}.

DOCUMENT NUMBER : DOCUMENT TITLE :

MIL-P-5315

MIL-R-6855

MIL-STD-81O(ReplacesMIL-E-5272)

N MIL-F-8615N91

MIL-H-5440

MIL-P-8721O(ReplacesMIL-P-5518)

kIL-E-7080

MIL-S-4040

MIL-S-8805(ReplacesMIL-S-6744)

Packing, Preformed, HydrocarbonFuel Resistant

Rubber, Synthetic Sheets, Strips,Molded or Extruded Shapes, GeneralSpecification for

Environmental Procedures andEngineering Guidelines

Fuel System Components; GeneralSpecification for

Hydraulic Systems, Aircraft, TypesI and II, Oesign and InstallationRequirements for

Pneumatic Power Systems, HighPressure

Electric Equipment, AircraftSelection and Installation of

Solenoid, Electrical , General

Switches and Switch Assemblies,Sensitive and Push (Snap Action),General Specification for

APPLICABILITY:

Any QPL Item.


Temperature, altitude, vibration,corrosion resistance, shock,humidity, shock.

Fuel resistance requirements.

Requirements (except for packing)and quality assurance for refueling


Air refueling system electricalequipment installation.

Any QPL itern.

Any QPL itern.

REFERENCED BY:

MIL-A-19736

MIL-A-19736

MIL-A-19736

MIL-A-19736

t41L-A-l9736

MIL-A-19736

MIL-A-19736

MIL-A-19736

MIL-A-19736


TABLE X. ~aui red documents and corresponding aoDlicabilitv data (continued.

DOCUMENT NUMBER:

MIL-R-6106

MIL-T-7928

MIL-C-5015

MIL-C-264B2

NNm

MIL-B-50B7

MIL-F-17B74

MIL-A-8591

MIL-A-BB65

MIL-T-6396

MIL-T-18847

DOCUMENT TITLE:

Relays, Electric, Aircraft,General Specification for

Terminals, Lug: Splices, Con-ductors; Crimp Style, Copper,General Specification for

Connectors, Electrical , AN Type

Connector, Electrical (Circular,Miniature, Quick Discannect,Environment Resisting), Recep-tacles and Plugs, General Spec-ification for

Bonding, Electrical and LightningProtection, Aerospace Systems

APPLICABILITY:

Any QPL item.

Any QPL itern.

Any QPL itern.

Any QPL itern.

Bonding to discourage buiId-up ofstatic charge.

R(EF.ERENCEOBY:

MIIL-A-19736

MIIL-4-19736

MlIL-A-l9736

M!IL-A-19736

t4JIL-A-19736

Fuel Systems: Aircraft Installation Installation and test reauirements; t&fL-A-19736and Te~t of fuel flow rate; quality assurance.

Airborne Stores, Suspension Tanker external stares loads. MIL-A-19736Equipment and Aircraft - StoreInterface (Carriage Phase): GeneralOesign Criteria for

Airplane Strength and Rigidity, Hose loads. MIL-A-19736Miscellaneaus Loads

Tanks, Aircraft Propulsion Fluid Requirements for removable tanks. MIL-A-19736System, Internal Removable, Non-Self-Sealing

Tanks, Fuel, Alrcraft, Auxi 1iary Requirements for external tanks. MIL-A-19736External Design and Installation of


—

DOCUMENT NUMBER :

MIL-STO-704

MIL-O-21625

MIL-P-7962

MIL-L-19537

TABLE X. Reauired documents and corresi2ondina am 1icabi1ity data (continued)..

MIL-H-4495

MIL-C-25162

MIL-M-18012

“MIL-N-25161

MIL-I-18B02

MIL-L-6730

00CUMENT TITLE:

Aircraft Electrical PowerCharacteristics

Oesign and Evaluation of Cartridgesfor Cartridge Actuated Devices

Primer Coating, Cellulose - NitrateModified Alkyd Type, Corrosion -Inhibiting, Fast Orying

Lacquer; Acrylic - Nitrocelluose,Gloss for (Aircraft use)

Hose Assembly, Rubber, AerialRefueling

Coupling, Reception, F1ightPressure, Refueling Type MA-2

Markings for Aircrew Station Dis-plays, Design and Configuration ofNozzle, Aerial Pressure, RefuelingType MA-2

Installation of Fuel and Oil Linesand Connections in Naval Aircraft

Lighting Equipment; Exterior Air-craft (General Specification for)


Category C. MIL-A-19736

Requirements and quality assurance. MIL-A-19736

Primer requirements for hose reels. MIL-A-19736

Lacquer requirements for hose MIL-A-1 9736

reels.

Type 1.

Any QPL itern.

Control panel requirement

Any QPL item. MIL-A-19736

Installation requirements. MIL-A-19736

Probe light requirements. MIL-A-19736

The remaining second tier references, tiered

Third Tier

MIL-F-18264 Finishes, Organic, NeaponsApplication and Color of

to MIL-A-19736, are for guidance and information.

Systems, Requirements and quality assurance. MIL-F-7179


TABLE X. Reauired documents and corresDondina acmlicabilitv data (contlnued}.

DOCUMENT NUMBER:

MIL-S-5002

MIL-A-83377

MIL-S-81733

MIL-S-8802

MIL-S-83430

MIL-C-5541

ASTM 8137

MIL-STO-1O5

ASTM 0244

DOCUMENT TITLE:

Surface Treatments and InorganicCoatings for Metal Surfaces ofWeapons Systems

Adhesive 8onding (Structural) forAerospace and Other Systems,Requirements for

Sealing and Coating Compound,Corrosion Resistant

Sealing Compound, Temperature-Resistant, Integral Fuel Tanks andFuel Cell Cavities, High Adhesion

Sealing Compound, ‘Integral FuelTank and Fuel Cell Cavities,Intermittent Use to 360”F

Chemical Conversion Coatings onAluminum AlIoys

Standard Test Method for Measure-ments of Weight of Coating onAnodical ly Coated Aluminum

Sampling Procedures and Tablesfor Inspection by Attributes

Standard Test Method for Measure-ment of Thickness of AnodicCoatings on Aluminum and OtherNonconductive Coatings on Non-Magnetic Basis Metals

APPLICABILITY:

Requirements and quality assuranceexcept for resistance-welded fayingsurfaces.

Adhesion requirements for fayingsurfaces.

Any QPL item.

Any QPL itern.


Class 1A, brush application.

Test soecimen and DrOcedUresections.

Inspection level 11; AQL of 1.5%.

Apparatus, factor affectingmeasurement, procedures andaccuracy sections.

REFERENCED BY:

MIL-F-7179

MIL-F-7179

MIL-F-7

MIL-F-7

79

79

MIL-A-8625

MIL-A-8625

MIL-A-8625


TABLE X. R uired urnn and orr~) data ntinued

I

DOCUMENT NUMBER :

FED-STD-151

ASTM B117

ASTM G23

Nw ASTM 02244

FED-STO-141

MIL-I-25017

MIL-I-276B6

ASTM D156

ASTM 03242

DOCUMENT TITLE: APPLICABILITY:

Metals, Test Methods Method 520, Electronic.Test forLocal Coating Thickness.

Standard Method of Salt Spray Apparatus, salt solution, con-(Fog) Testing ditions in chamber, period of

test sections.

Standard Practice for OoeratinQ ADDaratUS. qen@ral proceduresiLioht-Exoosed Aooaratus’(Carbo~ Methods 1. i and 3 sections.Ar~ Typej Hith”~~d Without Waterfor Exposure of Nonmetal1icMaterials

Standard Method for Calculationof Color Oifferen,cesfor Instru-mentalIy Measured Color Coordinates

Paint, Varnish, Lacquer, andRelated Materials; Methods forTesting of

Inhibitor, Corrosion, Fuel Soluble

Inhibitor, Icing, Fuel System

Standard Test Methods for SayboltColor of Petroleum Products (Say-bolt Chronometer Meter)

Standard Test Method for Acidityin Aviation Turbine Fuel

Summary of method and proceduresections.

Method 6192.

Any QPL itern.

Conformance of fuel system icinginhibitor; material requirements

Procedure for refined light oi1s.

Procedures.

REFERENCED BY:

MIL-A-8625

MIL-A-8625

MIL-A-8625

MIL-T-5624

MIL-T-5624MIL-T-6396

MIL-T-5624

MIL-T-5624


DOCUMENT NUMBER:

ASTM D1319

ASTM D822

TABLE X. Reouired documents and corresoondinq aDOliCabilitv data (continued~

ASTM A304(ReplacesQQ-S-624)

MIL-STD-l05

ASTM B4B7

ASTM B499

ASTM B504

DOCUMENT TITLE:

Standard Test Method for Hydro-carbon Types in Liquid PetroleumProducts by Fluorescent IndicatorAbsorption

Standard Practice for OperatingLight and Water Exposure Apparatus(Carbon Arc Type) for TestingPaint and Related Coatings andMaterials

Standard Specification for Al10YSteel Bars Subject to End-QuenchHardenabi1ity Requirements

Sampling Procedures and Tables forInspection by Attributes

Standard Methods for Measurementof Metal and Oxide Coating Thtck-ness by Microscopical Examinationsof a Cross Section

Standard Test Method for Measure-ment of Coatinq Thickness bv theMagnetic Method: Non-Magne~icCoatings on Magnetic Basis Metals

Standard Test Methods for Measure-ments of Thickness of MetallicCoatings by Coulometric Method

APPLICABILITY:

Materials,

Procedure,evaluation

sampling and procedures.

Manufacture,and chemical

exposure and evaluationof results sections.

general requirementsrequirement sections.

Inspection level 2, AQL of 1.5%.Inspection level 2, AQL of .65 and1%.

Preparation of cross-sections andmeasurements sections.

Calibration of instruments andmeasuring procedures section.

Calibration ofprocedures forsections.

instruments andmaking measurements

REFERENCED BY:

MIL-T-5624

MIL-A-8625

QQ-C-320

QQ-C-320

QQ-C-320

QQ-C-320

(X)-C-320


DOCUMENT NUMBER :

MIL-STO-1312

ASTM B578

ANSI B46.i

ASTM 02240

ASTM D412

ASTM D792

TABLE X. Ruirddumn nd rre~ ntinued~.

ASTM D51B

ASTM Dl149

MIL-P-5425

TT-N-95

ASTM 0395

ASTM 0471

00CUMENT

Fastener

Standardhardness

TITLE :

Test Methods

Test Method for Micro-of Electroplated Coatings

Surface Texture (Surface RoughnessWaviness and Lag)

Standard Test Method for RubberProperty - Hardness

Standard Test Methods for RubberProperties in Tension

Standard Test Methods for SpecificGravity (Relative Density) andOensity of Plastics by Displace-ment

Standard Test Method for RubberDeterioration - Surface Cracking

Standard Test Method for RubberDeterioration - Surface OzoneCracking in a Chamber

Plastic Sheet, Acrylic, HeatResistant

Naptha, Aliphatic

Standard Test Method for RubberProperty, Compression Set

Standard Test Method for RubberProperty, Effect of Liquids

APPLICABILITY:

Test 12.

Vicker indicatorload.

with 100 gram

Roughness requirements.

Conditioning and proceduressections.

Calibration, Method A and Tables1 and 2.

Conditioning and Method A sections

Method A.

Test specimen and proceduresections.

Any QPL itern.

REFERENCE BY:

QQ-C-320

QQ-C-320

MIL-H-8775

MIL-R-6B55

MIL-R-6B55x

%MIL-R-6B55 N ;

z:o 0Xmm n

s

MIL-R-6855 u

MIL-R-6855

MIL-R-6855

Requirements and quality assurance. MIL-R-6855

Method A. MIL-R-6855

Test procedures, test liquids and MIL-R-6855changes in tensile strength,elongation and hardness sections.


00CUMENT NUMBER:

FED-STD-151

MIL-STD-2175(ReplacesMIL-C-6021)

MIL-A-21180

MI L-F-7190

MI L-R-5315

MIL-R-6855

MIL-R-Z5988

MIL-R-83248

W-P-41 6

QQ-C-320

)4S33558

TABLE X. Reouired documents and corresoondinq aDDIfcabilitv data (continued>.

DOCUMENT TITLE:

Metal , Test Methods

Castings, Classification andInspection of

Aluminum Alloy Castings, HighStrength

Forging, Steel, for Aircraft andSpecial Ordnance Applications

Packing, Preforms, HydrocarbonFuel Resistant

Rubber, Synthetic Sheets, Strips,Molded or Extruded Shapes, GeneralSpecification for

Rubber, Flurosilicon Elastomer, Oiland Fuel Resistant, Sheet, Strips,Molded Parts, and Extruded Shapes

Rubber, FluorocarbonElastomer, HighTemperature, Fluid and CompressionSet Resistant


Chromium Plating, Electrodeposited

Pointers, Dial, Standard Oesign ofAircraft Instrument

APPLICABILITY:

Mets\ inspectionfuel resistance.

Requirements andinspection of.

Requirements and

Requirements and

Any QPL item.

Class 1.

REFERENCED BY:

requirements for MIL-F-8615

quality assurance, MIL-F-8615

quality assurance. MIL-F-8615

quality assurance. MIL-F-8615

z

MIL-F-8615 ~ ~v?m ~E

MIL-F-8615 ~ ~<1t-l zIn.

Requirements and quality assurance. MIL-F-8615

Requirements and quality assurance. MIL-F-8615

Class 2, Type II. MIL-F-8615

Class 2. MIL-F-88615

Letter design. MIL-M-18012


IAULL X. Feaulrea aocumenrs ana corresDonolna ao~ IlcaolIlrf oara \conrlnueoL.

Nwm

DOCUMENT NUMBER :

MIL-STD-203

MIL-STO-250

MIL-STD-411

MS33549

MS33786

MS29558 -MS29560

MS33581

MS29568

MS20995

MIL-N-25027

MS33540

00CUMENT TITLE:

Aircrew Station Controls and Dis-plays Assignment, Locations andActuation of; for Fixed WingAircraft

Aircrew Station Controls and Ois-plays for Rotary Wing Aircraft

Aircrew Station Signals

Case, Instrument, 2-314 Oial WithSump, Standard Dimensions

Fitting, Installation, Flared Tubeand Hose, Swivel

Fitting, O-Ring, Circular, Compres-sion Type, Single Groove, Tank

Fitting, Attachment, Molded, Tank,Thru Hole, Flush, O-Ring

Fitting, O-Ring, General Featuresof Construction

Fitting, Attachment, Molded Tank,Flush

Wire, Safety or Lock

Nut, Self-Locking, 250”F, 450”Fand 800”F

Safety Wiring and Cotter Pinning,General Practices for

APPLICABILITY:

Cockpit control and displayrelationship.

Cockpit control and displayrelationship.

Control knob requirements.

Entire document.

Entire document.

Entire document.

Entire document.

Entire document.

Entire document.

CRES requirements.

Self-locking feature requirements.

Safety method “section.

REFERENCE BY:

MIL-M-18012

MIL-M-18012

MIL-M-18012

MIL-T-6396

x

MIL-T-6396 ~ ~vym mS.1

MIL-T-6396 Q ~nr-l GW

MIL-T-6396

MIL-T-6396

MIL-T-6396

MIL-T-6396

MIL-T-6396

MIL-T-6396


Nwm

DOCUMENT NUMBER :

MS24665

TABLE X. fzeauired documents and corresDondinciarmlIcabilitv data

MIL-STD-81O

ASTM B117

MIL-A-8625

MIL-C-5541

MIL-P-8045

TT-S-735

ASTM D381

FED-STD-601

FED-STD-191

ANSI B46.1

DOCUMENT TITLE:

Switch, Toggle, Positive 8reak,Miniature Toggle Sealed, SinglePole

Environmental Test Methods andEngineering Guidelines

Standard Method of Salt Spray(Fog) Testing

Anodic Coatings, for Aluminum andAluminum AlIoys

Chemical Conversion Coating onAluminum and Aluminum Alloys

Plastic, Self-Sealing and Non-Se]f-Sealing Tank Backing Mater

Standard Test Fluids, Hydrocarbons

Fuels by Jet Evaporation, Gum In

Rubber, Stamping

Textile Test Methods

Surface Texture (Surface Rouahness.Waviness and Lay)

. .

APPLICABILITY:

Entire document.

~ntinued) .

REFERENCED BY:

MIL-T-6396

Salt fog, Method 509 (steel parts MIL-T-6396only).

Apparatus, factors affecting MIL-T-6396measurement, procedures and accu-racy sections.

Requirements and quality assurance. MIL-T-6396

Requirements and quality assurance. MIL-T-6396

Type 1, materials requirements. MIL-T-6396 n

Types I and III. MIL-T-6396

Use evaporation time of 45 minutes. MIL-T-6396

Methods 4111, 4121 and 8011. MIL-T-6396

Method 5100. MIL-T-6396

Surface roughness finishes. MIL-H-8775

The remaining third tier references, tiered to MIL-A-19736, are for guidance and information


TABLE X. R uir d men nd rr~1 li i1it~ data ntinued


First Tier (5o of 9b Documents)

MIL-L-22589 Launching System, Nose Gear Type,Aircraft

Seco nd Tier

607770

I MIL-A-8860 Airplane Strength and Rigidity,General Specification for

MIL-A-BB63 Airplane Strwgth and Rigidity,Ground Loads for Navy AcquiredAirplanes

MIL-STD-203 Aircrew Station Controls and Ois-plays; Assignment, Location andActuation of, for Fixed MingAlrcraft

MIL-STD-411 Aircrew Station Signals

MIL-T-81259 Tie-Downs, Aircraft Oesign,Requirements for

FIIL-B-8511O

Catapult accessory requirements,catapult spotting requirements.

Launchino system dimensionalrequiremintk.

Launching weights and center ofgravity.

Loads and strength requirements.

Location of controls for catapultaccessories.

Advisory 1ight requirements forcatapult accessories.

Holdback fitting restraint.


MIL-D-B708

MIL-L-22589

MIL-L-22589

MIL-L-22589

141L-L-22589

MIL-L-22589

MIL-L-22589

MIL-L-22589

>-a:z0

xn

The remaining second tier references, tiered to MIL-L-22589, are for guidance and information.


————

TABLE X. Reauired documents and corresDondirm ao~Iicability data (continued).


Third Tier

MIL-A-8860 Airplane Strength and Rigidity, Design weights. MIL-A-8863General Requirements for

MIL-C-81774 Control Panel, Aircraft, General Design location af controls. MI’L-STD-203Specification for

MIL-STD-1333 Aircrew Station Geometry for Zone 1. MIL-STD-203Military Aircraft

The remaining third “tier references, tiered to MIL-L-22589, are for guidance and information. T

Nw First e (51 of 9b Oocuments~Ti r

MIL-F-23447 Fire Warning Systems, Aircraft,Radiation Sensing Type, Test andInstailation of

Seco nd Tier

MIL-E-5400 Electronic Equipment, Aerospace,General Specification for

MIL-STD-704 Aircraft Electric Power Character-istics

MIL-STD-411 Aircrew Station Signals

MS25231-313 Lamps, Incandescent, CenterContact, Miniature Bayonet Base(T-3-l/4 Bulb)

141L-C-26482 Connectors, Electric, Circular,Miniature, Quick Disconnect

Ground and flight operationthe fire warning system.

of

Control amplifier and sensorinternal wiring.

Transient voltage shall not resultin a false alarm; power variation.

Fire warning signal requirements;legend-type warning system with“FIRE” in red.

Light signal lamp requirementsfor fire warning.

Any QPL item.

HIL-F-23447

MIL-F-23447

MIL-F-23447

MIL-F-23447

NIL-F-23447


TABLE X. ~eaui red documents and corresoandinq a~Dlicabilitv data (continued).

DOCUMENT NUMBER :

MIL-R-6106

DOCUMENT TITLE: APPLICABILITY: REFERENCED BY:

t41L-F-23447

MIL-F-23447

Relay, Electric, Aerospace,General Specification for

Any QPL itern.

Installation of electrical andelectronic components of thefire warning system.

MIL-E-7080 Electric Equipment, Aircraft,Selection and Installation of

Installation of electrical andelectronic components of thefire warning,system.

MIL-I-8700 Installation and Test of Elec-tronic Equipment in Aircraft,General Specification for

Wiring Aerospace Vehicle

141L-F-23447

Installation of fire warningsystem wiring.

MIL-k4-5088 MIL-F-23447x.~%

MIL-F-23447 : ?z~0.0xm

r)l-l

sVI

Ncdw

Environmental tests including:high and low temperature, highand low altitude, rate of climb,rzin, vibration, salt spray, andfungus resistance.



MIL-T-5624 JP-4 fuel used for flame tests. MIL-F-23447Turbine Fuel, Aviation, GradesJP-4, JP-5 and JP-5/JP-8

Standard Specification for AviationASTM D91O(ReplacesMIL-G-5572)

MIL-I-61B1

Grade 100 octane 9a501inc. MIL-F-23447Gasolines

Interference Control Requirements EMI requirements. MIL-F-23447Aircraft Equipment

All remaining second tier referenced, tiered to MIL-F-23447, are for guidance and information.

for Requirements 17 and 69 for printed MIL-E-5400wiring and internal wiring.

Third Tier

MIL-STO-454 Standard General Requirements


lAISLkX. Rulrdaumntn~ rre II 111 a ntlnueo

DOCUMENT NUMBER:

MIL-C-25050


MIL-I-25017

MIL-I-27686

ASTM D156

ASTM D3242

ASTM D1319

ASTM D1323(1)

MIL-I-6051

DOCUMENT TITLE:

Colors, Aeronautical Lights andLighting Equipment, General


Inhibitor, Corrosion, Fuel Soluble

Inhibitor, Icing, Fuel System

Petroleum Products, SayboltColor of

Standard Test Method for Acidityin Aviation Turbine Fuel

Hydrocarbon Types in LiquidPetroleum Products by FluroescentIndicator Absorption

Interference Limits and Methods ofMeasurements, Electrical and Elec-tronic Installation in AirborneWeapons Systems and AssociatedEquipment

APPLICABILITY:

Color and brightness of warningsignals.

Aeronautical explosion proof testsfor electronic equipment.

Any QPL itern.

Conformance of fuel system icinginhibitor.


Acid number requirements.


Weight percent of mercaptan sulfur

Limit reauirements for airvehicles:

The remaining third tier references, tiered to MIL-F-23447, are for guidance and information.

REFERENCED BY:

MIL-STD-411

MIL-E-70B0

MIL-J-5624

MIL-J-5624

,,

MIL-J-5624 n ~

MIL-J-5624

MIL-I-6181

(1) ASTM 01323 is canceled with no superseding document.


————

.

TABLE X. Reau bocuments and corresc)oired ndinq am licabilitv data (continued).

DOCUMENT NUMBER : DOCUMENT TITLE: APPLICABILITY: REFERENCED BY:

First Tier (52 of 96 DOcuments~

MIL-R-23761 Regulator, Voltage and Control Any QPL itern. HIL-D-8708Panel, Aircraft, Direct CurrentGenerator, General Specificationfor

Second and Third Tier$

Al1 second and third tier references, tiered to MIL-R-23761 , are for guidance and information.

IFirst Tier (53 of 9b Oocumentsl

Na MIL-C-Z866

S?:ond Tier

MIL-E-5400

MIL-E-4682(1)

MIL-STO-415

t41L-H-5088

MIL-I-6181

MIL-STO-704

Control Set, Appro?ch PowerANIASN-54(V)

Electronic Equipment, Aerospace,General Specification for

Electron, Tube and Transistors,Choice and Application of

Test Provisions for ElectronicSystems and Associated Equipment,Design Criteria for


Interference, Control Requirements,Aircraft Equipment

Aircraft Electrical powerReauirements

Requirements and quality assurance. MIL-O-8708 ~ ~-u?Z&l0 2SW

nEnvironmental service conditions MIL-C-23866 m >for Class 2 equipment.

Requirements and “qualityassurance. MIL-C-23866

Requirements. MIL-C-23866

External wiring requirements (un- MIL-C-23B66shielded interconnection cabllng).

Radiated interference vulnerability. MIL-C-23866

Requirements. hlIL-C-23B66


N

is

TABLE X. Reauired documents and corresDondina aDDlicabilitv data (continued) .


MIL-STD-7B5 Reliability Program for Systems and Calculated failure and reliability(Replaces

MIL-C-23866Equipment Development and Pro-

MIL-R-22256)data; Test level IV, Table V.

duction

MIL-STD-756 Reliability Modeling and Prediction Calculated failure and reliability MIL-C-23B66data.

MIL-M-7793 Meter, Time Totalizing Any QPL itern. MIL-C-23866

MIL-T-19229 Transmitter, Angle af Attack or Any QPL itern. MIL-C-23866Sideslip, Local for angle of attack transmitters.

MIL-T-5422 Testing, Environmental , Airborne Environmental testing require- MIL-C-23866Electronic and Associated Equip- ments - temperature-altitude;ment vibration; shack; humidity; salt

spray; explosion; sand-dust;fungus.

MIL-STD-781 Reliability Testing for Engineer- Procedure I. MIL-C-23866(Replaces ing Development, QualificationMIL-R-23094) Production

The remaining second tier references, tiered to MIL-C-23866, are for guidance and information.

Third Tier

MIL-C-7078 Cable, Electric, Aerospace Vehicle, Cable requirements. MIL-W-50B8General Specification for

MIL-C-27500 Cable, Electric, Shielded and Un- Cable requirements. MIL-14-50B8shielded, Aerospace

MIL-E-5400 Electronic Equipment, Aerospace, Class 2. MIL-T-5422General Specification for

>‘u-u~0

xn


TABLE X. Reauired documents and corresDondina aDollcability data (continuedl.


ASTM D91O Standard Specification for Aviation Grade 100/130.(Replaces Gasolines

HIL-T-5422

MIL-G-5572)

MIL-STO-1472 Human Engineering Design Criteria Human engineering requirements for MIL-STD-415far Military Systems, Equipment electronic systems.and Facilities

(1) MIL-E-4682 is cancelled WIth no superseding document.


141L-E-24021 Electric Power Monitors, External Any QPL item. MIL-D-8708 x

Aircraft >~-0V?

Se nco d and Third Tier!mZ-0

;zAll second and third tier references, tiered to MIL-E-24321 , are for guidance and information. .00 z

First Tier (55 of 9b Documents~v

MIL-W-25140 Height and Balance Control System Requirements for maximum aft and HIL-D-8708(for Aircraft and Rotocraft) foruard center of gravity for

service loadings; ~eight-andbalance data.

Breakdown Structures for Hork breakdown structure system MIL-H-25140

Sec ond Tier

MIL-STD-881 WorkDefense

The remaining second tier

Third Tier

All third tier references, tiered to MIL-H-Z5141),are for guidance and information.

Materiel Items requirements.

references, tiered to HIL-W-25140, are for guidance and information.


r ‘“”- ‘--I TABLE X. Reauired documents and corresaondina aDoIicabilitv data (continued).


First Tier (56 Of 96 Documents~

MIL-P-26292

Se cond Tier

MIL-P-83207(1)

MIL-P-83206(2)

g&

tiIL-M-7793

HN-T-400/4

MS33611

MIL-A-8625

MIL-C-5541

MIL-T-8606

141L-STO-1247

TT-S-1732(ReplacesTT-A-580)

Pitot and Static Pressure Systems,Installation and Inspection af

Pitot-Static, Nose Boom, Compen-sated, General Requirements for

Pitot-Static Tube, N-Shaped,Compensated, General Specificationfor

Heter, Time Tatali.zing

Tube, Aluminum Allay, Drawn,Seamless

Tube Bend Radii

Anodic Coatings, for Aluminum andAluminum Al10YS

Chemical Conversion Coatings

Tubing, Steel, Carrosion-Resistant(18-8 Stabilized and Extra LowCarbon)

Markings, Functions and HazardousDesignations of Hose, Pipe andTube Lines for Aircraft Missileand Space Systems

Sealing Campound, Pipe Joint andThread, Lead Free General Purpose

APPLICABILITY:


Performance requirements.

Performance requirements.

Any QPL item.

Tubing requirements.

Minimum bend radius.



Tubing requirements.

Color requirements for pitat andstatic pressure lines.

Requirementsfor materialparts.

and quality assuranceto be used an threaded

REFERENCE BY:

MIL-O-870B

MIL-P-26292

MIL-P-26292

MIL-P-26292

MIL-?-26292

MIL-P-26292

MIL-P-26292

MIL-P-26292

MIL-P-26292

MIL-P-26292

MIL-P-26292


I

I

I

I

I

I

I

I

TABLE X. Ruirddumnsan rr~ Ii i1ity data ntinue ).

DOCUMENT NUMBER : DOCUMENT,TITLE: APPLICABILITY: REFERENCED BY:

MIL-$-22473 Sealing, Locking, and Retaining Requirements and quality assurance MIL-P-26292Compounds (Single Component) for use in high vibration applica-

tions.

AN6270 Hose Assembly, Detachable Swivel Flexible hose assembly require- MIL-P-26292Fitting, Low Pressure ments.

NIL-H-25579 Hose Assembly, Tetrafluoroethylene, Any QPL itern. MIL-P-26292High Temperature, Medium Pressure

The remaining second tier references, tiered to MIL-P-26292, are for guidance and information.

Third Tier

MIL-C-5541

MIL-STD-105

ASTM B137

ASTM B244

ChemicalAluminum

Sam91incr

Conversion Coatings onand Aluminum Alloys

Procedures and Tables forInspection by Attributes

Standard Test Method for Measure-ments of kleightof Coating onAnodically Coated Aluminum

Standard Test Method for Measure-ment of Thickness of AnodicCoatings on Aluminum and OtherNonconductive Coatings

FEO-STD- 151 Metals, Tests Methods

Class 1A, brush applications.

Inspection level 2, AQL ofInspection level per Table

Specimens and procedures.

1.5%.II.

Apparatus, factors affectingmeasurement, procedures andaccuracy sections.

Method 520.

ASTM B117 Standard Method of Salt Spray (Fog) Apparatus, salt solution, con-(Replaces Testing ditions in salt spray chamber,Method 811 ofFED-STD-I51)

continuity and period of test andevaluation sections.

MIL-A-8625

MIL-A-8625MIL-S-22473

MIL-A-8625

MIL-A-8625

MIL-A-8625

MIL-A-8625

r-l


Nam

TABLE X. Reauired dacuments and corresrmndirm aao1icabilitv data (continuedl.


ASTT4G23 Standard Practice for OperatingLight-Exposure Apparatus (Carbon-Arc Type) Hith and Nithout Haterfor Exposure of Nonmetal1icMaterials

ASTM D822 Standard Practice for OperatingLight and Hater Exposure Apparatus(Carbon Arc Type) for TestingPaint and Related Coatings

ASTM D2244 Standard Method for Calculation ofColor Differences for Instrumen-tally Measured Color Coordinates

FED-STO-141 Paint, Varnish, Lacquer andRelated !4aterials;Methods forTesting of

FED-STD-595 Colors

MIL-H-6B75 Heat Treatment of Steels (Aero-space Practice, Pracess for)

MIL-STD-753 Corrasion-Resistant Steel Parts:Sampling, Inspection and Testingfor Surface Passivation

APPLICABILITY:

Methods 1, 2 and 3.

Procedure, exposure and evaluationsections.

Summary and procedure sections.

Hethod 6192.

Color nos: 15102, 14187, 13655,12197, 11136. 10049, 16473 and17038.

Temperature cantrol requirements.

Method 102 or 103.

REFERENCED BY:

MIL-A-8625

MIL-A-B625

MIL-A-B625

MIL-A-B625

MIL-STO-1247

MIL-T-B606

MIL-T-8606

a=-0

2zax(-)

(1) MIL-P-83207 is cancelled with no superseding document.(2) MIL-P-83206 is cancelled with na superseding document.

The remaining third tier references, tiered to liIL-P-26292, are for guidance and information.

First Tier (57 of 9b Documental

HIL-P-26366 Propeller Systems, Aircraft, Vibratory stress survey require- MIL-D-8708General Specification for ments (ground and flight tests).


TABLE X. Reauired documents and corresoondina aDoIicabilitv data (continued~.


s~x

Al1 second and third tier references, tiered to MIL-P-26366, are for guidance and information.

Fir t Ti r f~

MIL-T-81571 Thermal Protective Systems, Air-craft Cockpit, General Specifi-cation for

Second Tier

MIL-F-7179 Finishes, Coatings, and Sealantsfor the Protection of AerospaceVehicles Systems

FED-STO-595 Colors

FEO-STO-141 Paint, Varnish, Lacquer and RelatedMaterials, Methods for Testing of

ASTM 02240 Rubber Praperty-Ourometer Hardness(ReplacesASTM D676)

ASTM D412 Rubber Properties in Tension

ASTM D624 Rubber Property-Tear Resistance

ASTM D573 Rubber-Deterioration in an Air Oven

ASTM D395 Rubber Property-Compression Set

Operation of nuclear thermalradiation pilot or cockpitprotective system.

Protection requirements formetals when placed in hastileenvironments (corrosion).

Colors 37038, 36440, 17875 and37B75.

Methods 6301 and 4061.

Hardness “A”.

Methods A and B.


Hardness “A,” 70 hr test.

Method B, Z ariginal elongation.

MIL-D-8708

MIL-T-81571

MIL-T-81571

MIL-T-81571

t41L-T-81571

t41L-T-81571


TABLE X. Reauired 60cuments and corresDondina amlica bilitv data (continued)

DOCUMENT NUMBER :

MIL-S-18471

MIL-A-23121

MIL-I-8500

MIL-C-8779

MIL-STD-2161(ReplacesMIL-C-18263)

MIL-A-8865

ACEL ReportNAEC-ACEL-533

DOCUMENT TITLE:

System Aircrew Automated Escape,Ejection Seat Type: GeneralSpecification for

Aircrew Environmental Escape andSurvival Cockpit Capsule System;General Specification for

Interchangeabi1ity and Replace-ability of Component Parts forAerospace Vehicles

Color, Interior, Aircraft, Require-ments for

Paint Schemes and Exterior Markingsfor U.S. Navy and Marine CorpsAircraft

Airplane Strength and RigidityMiscellaneous Loads

Anthropometry of Naval Aviators

APPLICABILITY:

Ejection seat clearance envelope.

Emergency escape and survivalmission of cockpit capsule.

Thermal protective system partsinterchangeabi1ity requirements.

Interior colors not previouslydefined.

Exterior colors not previouslydefined.

Open position loads (longitudinal/’vertical).

Thermal protective system compat-ibi1ity requirements for upper

REFERENCED BY:

MIL-T-81571

MIL-T-B1571

MIL-T-81571

MIL-T-81571

MIL-T-81571

MIL-T-81571

MIL-T-81571

and lower percentiles.

The remaining second tier references, tiered to MIL-T-81571 , are for guidance and information.

Third Tier

ASTM 0412 Rubber Properties in Tension Methods A and B. ASTM 0575

MIL-C-81590 Cockpit Canopy System, Fixed Wing Transparency construction design. MIL-A-23121Single and Multiplace, FighterAircraft and Trainer Aircraft,General Specification for

Al 1 third tier references, tiered to MIL-T-81571 , are for guidance and information.

n


TABLE X. Reauired dacuments and corresoondino a!mlicabi1itv data (continued).

DOCUMENT NUMBER: DOCUMENT TITLE: APPLIC4BILIlY:

Fir t Ti r~1

MIL-B-81757 Batteries and Cells, Storage, Any QPL itern.Nickel-Cadmium, Aircraft, GeneralSpecification far

Zeco d an nd Third Tiers

All second and third tier references, tiered to MIL-B-81757, are for guidance and

First Tier (60 Of 9b”Documents-)

N MIL-E-8191O Electrical Power Generating andam Control Equipment, Aircraft,

General Specificatian for

sp~~nd Tier

MIL-STD-81O Environmental Test klethodsEngineering Guidelines

MIL-L-23699 Lubricating Oi1, Aircraft,Engines Synthetic Base

and

Turbine

MIL-STD-462 Electromagnetic InterferenceCharacter sties, Measurement of

MIL-STD-461 Electromagnetic Emission and Sus-ceptibility Requirements for theControl of Electromagnetic Inter-ference

Requirements and qual

REFERENCED BY:

MIL-D-8708

nformation.

Method 513, Procedure 1/11,Acceleration; Method 510,PrDcedure 1, Dust; Method 509,Procedure 1, Salt Fog; Method516, Procedure 1/111, Shock:Method 508, Procedure I, Fungus.

Any QPL item.

ty assurance. MIL-D-8708

MIL-E-8191O

MIL-E-8191O

MIL-E-8191O

FIIL-E-8191O

Methods CED3 and RE02.

Broadband conducted and radiatedemission requirements for CE03and RE02.

n


TABLE X. B?QUired documents and corresDondina am Iicabi1itv data (continued}.

DOCUMENT NUMBER : DOCUMENT TITLE: APPLIL4BILIlY: REFERENCED BY:

The remaining second tier r’eference$,tiered to MIL-E-8I91O, are for guidance and information.

Third Tier

All third tier references, tiered to MIL-E-8191O, are for guidance and information.


MIL-C-83413 Connectors and Assemblies, Elec- Any QPL itern. ,. MIL-D-8708trical Aircraft Grounding, GeneralSpecification for

N S.ecod an “nd Third Tiers xm >~0

Al1 second and third tier references, tiered to 1.IIL-c-83413,are for guidance and information.-0-uC3-,.-.z&Y.

First Tier (62 Of qh0

Documents)_ .0x~

,,

MIL-B-83769 Batteries, Storage, Lead-Acid,n

Any QPL,item. MIL-O-8708 s

General Specification for :

Seco nd and Third TierS

Al1 second and third tier references, tiered to MIL-B-83769, are for guidance and information.


——— ———.

TABLE X. Reauired documents and corresaondina aaoIicabiIitv data (continued~.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLI~BILITY: REFERENCED BY:

First Tier (63 of 96 Documents )

DOD-C-B5050 Chargers, Battery, Nickel-Cadmium, Any QPL itern. MIL-D-8708Aircraft, General Specification for

Seco nd and Third Tier$

Al1 second and third tier references, tiered to DOD-C-85050, are for guidance and information.


MIL-I-B670 Installation of Fixed Guns and Boresight retention. 141L-D-8708Associated Equipment in Naval z

Aircraft >;Ty2

Second and Third Tiers =9a-

0

All second and third tier references, tiered to MIL-I-8670, are for guidance and information.Xm nn G

:

First Tie“r(65 Of 96 DOCuments)

kiIL-I-85071 Inverters, Aircraft, OC ta AC, Any QPL itern. KIL-O-8708General Specification for

Seco nd and Third Tier$

All second and third tier references, tiered to MIL-I-85071 , are for guidance and information.

First Tier (66 of9 6 Documents~

DOD-B-85584 Battery Relay Control Unit, Any QPL itern. hlIL-O-8708Aircraft

Seco nd and Third Tiers

Al1 second and third tier references, tiered ta DI)O-B-85584,are far guidance and information.


TABLE X. Reauired documents and corresDondino aaolicabilitv data (continued~.


First Tier (67 of 9b DrjcumentQ

MIL-STD-454 Standard General Requirements for Protection system requirements; MIL-D-8708

Electronic Equipment Requirements 1 and 8.

~~cond and Thjrd Tiers

Ali second and third tier references, tiered to MIL-STD-454, are for guidance and information.


NU7N

MIL-STD-2165 Testability Program for Task 103 Testability Data HIL-D-870B

Electronic Systems and Collection and Analysis x

Equipments Planning. >yTwp

S~~~nd and Tnir@ ?~o~~mZm0-

0;-

A11 second and third tier references, tiered to MIL-STD-2165, are for guidance and information. nn G

First Tier (69 of 9bG

OQcuments)-.

MIL-STD-704 ~~~jgft Electric Power Character- Aircraft electrical power con- MIL-D-8708formance via steady state andtransient power character sties(for voltage, frequency, etc.).Alternate and emergency powersystems. Electric power minimumduring ground time. Power limitsexceeded (external power protec-tion, relay control circuits,etc.).

Sec ond and Third Tiers

All second and third tier references, tiered to 141L-STD-704, are for guidance and information.


TABLE X. Reauired documents and corresDondina aDoIicability data (continued~.



00D-STD-2167 Oefense System Software General requirements, MIL-O-870EDevelopment detai1ed requirements.

Al1 second and third tier references, tiered to DoD-STD-Z167, are for guidance and information.

First Tier (71 of 9b Oocuments~

Environmental Test Methods and Electrical system installation MIL-D-8708MIL-STD-810

Eu

Engineering Guidelines testing requirements (as speciftedin the applicable equipment... .

I specl~lcationl.

Second and Third

Al1 second and third tier references, tiered to MIL-STD-81O, are for guidance and information.


n

MIL-STO-877 Antenna Subsystem, Airborne Cri- Requirements and quality assur- MIL-D-8708terla for Oesign and Location of ante for installed antenna

systems.


DOCUMENT NUMBER :

TABLE X. Reau ired documents and corresvondinq aoDlicabilitv data (continued).

Second Tier

MIL-STD-454

MIL-L-7808

MIL-H-5606

MIL-H-8446(1)

MIL-J-5624

TT-I-735

O-E-760

00CUMENT TITLE:

Standard General RequirementsElectronic Equipment

for

Lubricating Oil, Aircraft TurbineEngine, Synthetic Base

Hyd;aulic Fluid, Petroleum Base,Aircraft, Missile and Ordnance

Hydraulic Fluid, Ijonpetroleum Base,Aircraft

Turbine Fuel, Aviation, GradesJP-4 and JP-5

Isopropyl Alcohol

Ethyl Alcohol (Ethanol): Denatured


Requirement 1 (Safety Design); MIL-STD-B77Requirement 7 (Interchange-abi1ity); Requirement 9 (Work-manship).


Any QPL itern. MIL-STO-B77

Nonpetroleum based hydraulic MIL-STD-877fluid.

Grade JP-4 jet fuel. MIL-STO-877

Requirements and quality assurance. MIL-STD-877

Requirements and quality assurance. MIL-STD-877Alc~hol; Proprietary Solvents andSpecial Industrial Solvents


TABLE X. Reauired documents and corresDondina aoolicabilitv data (continued).

DOCUMENT NUMBER : DOCUMENT TITLE:

O-M-232 Methanol (Methyl Alcohol)

MIL-B-50B7 Bonding, Electrical, and LightningProtection, for Aerospace Systems

MIL-E-6051 Electrical-Electronic SystemCompatibility and InterferenceControl Requirements for Aero-nautical Weapons Systems

MIL-R-7705 Radomes General Specificationfor

R


Requirements. MIL-STO-877

Bonding for metallic elements MIL-STD-877which are part of or adjacent tothe antenna subsystem.

Interference control for the MIL-STD-877design and location of antenna sub-systems; the design shall minimizethe need for IC devices.

Requirements for radomes and MIL-STD-877electromagnetic windows.

GiThe remaining second tier reference$, tiered to MIL-STO-877, are for guidance and information.

Jhird Tier

FEO-STD-141 Paint, Varnlsh, Lacquer and Related Method 1022 (Sampling and Inspec- TT-I-735Materials, Methods for Testing of tions); Method 4261 (Appearance).

MIL-STD-105 Sampling Procedures and Tables Level 1, AQL 2.5%. TT-I-735for Inspection by Attributes Level S-2, AQL 4%.

FED-STD-791 Lubricants, Liquid Fuels, and Method 3253 (Water Content). TT-I-735Related Products; Methods ofTesting

ASTM D1613 Acidity in Volatile Solvents and Reagents and procedure.Chemical Intermediates Used inVarnish, Paint, Lacquer andRelated Products

TT-I-735O-E-760

ASTM 01078 Distillation Range of Volatile Safety and procedures.Organic Liquids

TT-I-735


NG-1m

DOCUMENT NUMBER:

ASTM D891

TA8LE X. Reauired documents and corresDondino aimlicabilitv data (continued).

ASTM D1296

ASTM D130(ReplacesASTM D1616)

ASTM 01209

ASTM D1353

MIL-STD-105

ASTM D1193

ASTM E346

DOCUMENT TITLE:

Standard Test Methods for SpecificGravity, Apparent, of LiquidIndustrial Chemicals

Odor of Volatile Solvents andDiluents

Standard Method for Detection ofCopper Corrosion From PetroleumProducts by the Copper StripTarnish Test

Color of Clear Liquids (Platinum-Cobalt Scale)

Nonvolatile Matter in VolatileSolvents for Use in Paint, Varnish,Lacquer and Related Products

Sampling Procedures and Tables forInspection by Attributes

Reagent Water

Standard Methods for Analysis ofMethanol


Method A. TT-I-735

Procedure. TT-I-735O-M-232

Corrosion standards. TT-I-735

Platinum-cobalt reference standards O-E-760and procedures.

Safety and procedure. O-E-760O-M-232

Level S-4. O-M-232

Reagents and requirements. O-M-232

Procedures for % of acetone, O-M-232acidity, carbonizables, colordistillation range, ethanol, permaganate time, specific gravity,water.

tiered to MIL-STD-877, are for guidance and information.The remaining third tier references,

(1) This document has been canceled with no superseding documents.

%t-l


TABLE X. Reauired documents and corresDondina aDD\iCabilitV data (continuedl.


Fi”rst Tier (73 of gb DocumentQ

MIL-STO-882 System Safety Program Requirements

Seco nd Tier

There are no documents referenced to hiIL-STD-882.

First Tier (74 of 9b’Documents~

MIL-STO-1385 Preclusion of Ordnance Hazards inElectromagnetic Fields; GeneralReauirements for

second Tier

MIL-I-23659 Initiators, Electric, GeneralDesign Specification for

MIL-STO-1512 Electroexplosive Subsystems,Electronically Initiated Oesign,Requirements and Test Methods

OD 30393


Critical hardware, softwareand MIL-O-8708procedure requirements; reportformat to be task 209.

Requirements for avoiding hazards MIL-D-8708 xof electromagnetic rciiatioato >;ordnance. -

Verification of EEDs havingMNFS rating lA/lW to be inaccordance with electricalcharacteristics section.

Test Method 2003 for EEDs MNFS MIL-STO-1385rating other than lA/lli.

Method and techniques incorporated FiIL-STD-1385in designs.

The remaining second tier references, tiered to MIL-STO-1385, are for guidance and information.

Third Tier

FIIL-sTD-202 Test Methods for Electronic and Method 301, Dielectric Withstanding MIL-I-23659Electrical Component Parts Voltage; Method 303, BridgeCon-

tinuity: Method 302, Test ConditionB, Bridge Circuit Resistance.

All third tier references, tiered to MIL-STD-1385, are for guidance and information.


TABLE X. Reauired documents and corresoondina aoDlicabilitv data (continued~.



MIL-STD-l472 Human Engineering Design Criteria Emergency egress system. MIL-D-8708for Mi1itary Systems, Equipmentand Facilities

Second Tier

MIL-A-23121 Aircrew Environmental, Escape and Requirements for escape capsules. MIL-STD-1472Survival Cockpit Capsule System:General Specification for

The remaining second tier references, tiered to MIL-STD-1472, are for guidance and information.

Thiri Tier

YIL-C-81590 Cockpit Canopy System, Fixed fling Transparency construction require- MIL-A-23121Single and Multiplace, Fighter, ments.Attack and Trainer Airciaft,General Specification for

MIL-D-81514 Device, Restraint Harness, Take-Up Shoulder restraint device require- MIL-A-23121Inertia Locking, Pawered- ments.Retracting: General Specificationfor

The remaining third tier references, tiered to MIL-STD-1472, are for


t41L-sTD-1757 Lightning (qualificationTest Appendix A.Techniques for Aerospace Vehiclesand Hardware

Second and Third Tier\

guidance and information.

MIL-O-8708

Al1 second and third tier references, tiered to ‘MIL-STD-1757, are for guidance and information.


——

TABLE X. Reauired documents and corresoondina aoolicabilitv data (continuedl.

DOCUMENT NUMBER : DOCUMENT TITLE: APPLICABILITY:


MIL-STD-l760 Aircraft/Store Electrical Inter- Armament control systemconnecting System tion demonstration.

Second and Third Tlert

All second and thi,rd tier references, tiered to MIL-STD-1760, are for guidance

First Tier (78 of 9& Documental

MIL-STD-1795 Lightning Protection of AerospaceVehicles and Hardware

S03 nd Tier

MIL-E-6051 Electromagnetic Compatibi1ityRequirements, Systems

MIL-STO-1757 Lightning Qualification TestTechniques for Aerospace Vehiclesand Hardware

REFERENCED BY:

installa- HIL-O-8708

and information.

Lightning protection program. MIL-O-8708

.->~:7zm

E?4CControl Plan requirements, MIL-STD-1795 : ;as applicable. n

n GZone definitions. I’IIL-STD-1795 ~

The remaining second tier references, tiered to MIL-STO-1795, are for guidance and information.

Third Tier

All third tier references, tiered to MIL-STD-1795, are for guidance and information


I

Nm0

TABLE X. Reauired dacuments and corresDondinq aDDlicabilitv data (continuedl.



DOD-STD-2169 High Altitude Electromagnet cEnvironment

5eco nd and Third Tiers

Al1 secand and third tier references, tiered to

First Tier (80 of 96 Documental

MIL-STD-1388-1 Logistic Support Analysis

Second and ThirclTiers

All seccnd and third tier references, tiered to


Pulse NEMP environment requirements. MIL-D-B708

DOD-kTD-2169, are for guidance and information.

Task 501. MIL-O-8708

MIL-STD-1388-1, are for guidance and information.

First Tier (81 of 9b Dacuments)

US90298 Connector, receptacle, Electric Grounding jack. MIL-E-6051Connectar

&co nd Tier

AN960 14asher,Flat Al al10Y untreated washer. MS9029B

MS25082 Nut, Plain, Hexagon, Electrical Brass oxide plated nut. MS90298Thin


R

TABLE X. Reauired documents and corresr)ondinaaDDliCabilitY data (continued).


QQ-B-613 Brass, Leaded and Nonleaded: Flat Brass requirement. MS90298Products (Plate, Bar, Sheet, Strip)

QQ-B-750 Bronze, Phosphor; Bar, Plate, Rod, Composition A. MS90298Sheet, Strip, Flat Wire, andStructural and Special ShapedSections

QQ-P-416 Plating, Cadmium (Electrodeposi ted) Type II, Class 2. MS90298

MS3943 Cannector, Plug and Cap Electric, Test plug; insertion and removal MS90298Grounding forces.

MIL-STD-105 Sampling Procedures and Inspections Sampling - visual and mechanical, MS90298by Attributes insertion and withdrawal force,

torque and life test.

The remaining second tier references, tiered to MS90298, are for guidance and information.

Third Tier

QQ-A-25015 Aluminum Alloy ALCLAD 2024, Plateand Sheet

QQ-B-626 Brass, Leaded and Nonleaded: RodShapes, Forgings and Flat Productswith Finished Edges

MIL-F-495 Finish, Chemical, 81ack, for Copper

MIL-S-5002 Surface Treatments and InorganicCoatings for Metal Surfaces ofWeapons Systems

Condition T3 or T4 aluminum alloy. AN960

Brass requirement, Copper Alloy MS25082360.

Black oxide coating. MS250B2

Steel cleaning requirements for QQ-P-416cadmium plating.


TABLE X. Reauired documents and carresDondinu aDDlicabilitv data (continuedl.

NmN

DOCUMENT”NUMBER: DOCUMENT TITLE: APPLICABILITY:

MIL-S-7720 Steel, Carbon-Resisting (18-8) CRES (Plug and cap).Bars, Wire and Forging Stock(Aircraft Qua]ity)

The remaining third tier references, tiered to MS90298, are for guidance and information.

First Tier (82 of 96 Documental

hiIL-HDBK-235-2 Electronic (Radiated) Environment ExternalConsiderations for Design and electromagnetic“Procurement of Electrical and environments.Electronic Equipment, Subsystemsand Systems, Part 2

Second and Third Tierf

Al1 secand and third tiers, tiered to KIL-HDSK-225-2, are for guidance and information.


AR-40 Al1 Heather Carrier Landing Requirements, qualityInactive for System Airborne Subsystem, assurance provisions.New Design, General Requirements foreffective1 July 1979

First Tier (84 of 9b Oacumentsl

IRIG-STD-106 Range Commanders Counci1 Entire document.Telemetry Standards

Second and Third Tiert

REFERENCED BY:

MS3493

MIL-O-8708

MIL-O-870B

MIL-O-8708

All second and third tier references, tiered to IRIG-STD-106, are for guidance and information.


TABLE X. Reauired documents and corresoondina aoDIicability data (continue~.


Fir Ti r f~1

OPNAVINST 3070.1 Operations Security


NAVAIRINST 3710.1 Contractor’s Flight Operations


MIL-A-18717 “Arresting Hook Installations,Aircraft

mc1 5eco nd Tieru

MIL-A-3a~0 Airplane Strength and Rigidity

I!IL-B-8906 aolt, Tensile, Steel, 220 KSI Ftu,450”F, External Wrenching, FlangedHead

MIL-N-3922 Nut, Self-Locking, Steel, 220 KSIFtu 450”F

MIL-S-5002 Surface Treatments and InorganicCoatings for Metal Surfaces ofkleaponSystems

MIL-STD-203 Aircrew Station Centrals and Ojs-plays: Assignment, Location andActuatian af, for Fixed WingAircraft

APPLICABILITY:

Chapter 11 - OPSEC dactrine.

Entire NAVAIR INSTRUCTION.

Arresting loading requirementsand quality assurance.

Limits for the tai1 whe?l load

REFERENCED 3Y:

MIL-O-8708

MIL-O-3703

MIL-O-8708

resulting from the hook lacatians;a-

0Q

nose wheel load/envelape ar arrested zlandings definition: installation

n Gstrength requirements. :



Surface treatment requirements MIL-A-13717for metallic surfaces includingbolts, nuts and washers.

Location af arresting hook control MIL-A-18717in the cockpit.


Nm&

TABLE X. Reauired documents and corresoondinq aoDlicabilitv data (continued).


MIL-L-6730 Lighting Equipment; Exterior, Air- Relationship of arresting hook MIL-A-18717craft (General Requirements for) control and angle of attack

approach lights.

S0-8706 General Specification for Design Arresting hook installation drawing MIL-A-18717Examinations, Engineering, Air- requirements.craft Weapon Systems

MIL-H-25194 Hook Point, Aircraft Arresting Any QPL item. MIL-A-18717

14XL-D-23D03 Deck ‘CoveringCompound, Non-Slip, Any QPL itern. MIL-A-18717Lightweight

All remaining second tier documents, referenced to MIL-A-18717, are for guidance and information.

Third Tier

MIL-A-8863 Airplane Strength and RigidityGround Loads for Navy ProcuredAirplanes

MIL-A-8865 Airplane Strength and RigidityMiscellaneous Loads

MIL-A-8866 Airplane Strength and RigidityReliability Requirements, RepeatedLoads and Fatigue

MIL-A-8625 Anodic Coatings, for Aluminum andAluminum Alloys

MIL-C-5541 Chemical Conversion Coatings onAluminum and Aluminum Alloys

Loads for carrier-based land planes MIL-D-8860(arresting and catapulting loads).

Miscellaneous loading conditions MIL-D-8860including tail wheel and nosewheel loads.

Requirements for preventing of MIL-D-8860fatigue and repeated load damage.

Anodized coating for aluminum MIL-S-5002and aluminum alloys.

Chemical treatment coating of MIL-S-5002aluminum and aluminum al10YS.


I)UJLL A. neoulreo oocumenrs ano corresponolnu aDCl I}caolllrv oara [conrlnueo>.

DOCUMENT NUMBER:

MIL-C-81706

MIL-M-3171

MIL-M-45202

MIL-H-881O

MIL-S-3950

MIL-S-8805

MIL-S-22885

MS25318

MIL-I-6868

00CUMENT TITLE:

Chemical Conversion Materials forCoating Aluminum and AluminumAl10YS

Magnesium Alloy, Processes forPretreatment and Prevention ofCorrosion on

Magnesium Alioy, Anodic Treatmentof

Handles, Control, Aircraft

Snitch, Toggle, General Specifica-tion for

Switches and Switch Assemblies,Sensitive and Push, Snap Action,General Specification for

Switch, Pushbutton, 11luminated,General Specification for

Light, Approach, 28V

Inspection Process, MagneticParticle

APPLICABILITY:

Class 1A treatment by Method 8application.

Surface treatment of magnesiumal10YS; Type I or VI process fortouchup .

Anodic coating of magnesium al10YS,specifically parts subjected toabrasion, erosion or wear.

Control handle requirements withwarning light on handle.

Any QPL

Any QPL

tern.

tern.

Any QPL item.

AngIe of attack approach 1ights inred, yellow and green.

Non-destruction inspections ofarresting hook assembly.

REFERENCE 8Y:

MIL-S-5002

MIL-S-5002

MIL-S-5002

MIL-STD-203

MIL-STO-203

MIL-STD-203

MIL-STO-203

MIL-L-6730

MIL-L-6730

All remaining third tier documents, referenced to MIL-A-18717, are for guidance and information.


.TABLE X. Reauired documents and corresoondina aDDlicabilitv data (continued~.

Nmm


First Tier (88 of q6 Oocuments)-

MIL-B-85110 Bar, Repeatable Release HoldbackAircraft Launch, General DesignRequirements for

First Tier (B9 Of 96 Documents)

MIL-STD-470 Maintainabi1ity Program Require-ments (for Systems and Equipments)

Second Tier

MIL-S70471 HaintainabiIity Verificati”on/Demonstration/Evaluation

Third Tier

APPLIC4BILI~:

Requirements for strength, servicelife and carrier suitabilityrequirements.

Maintainabi1ity demonstration;data CO1lection requirements.

Incorporation and enforcementofmaintainability requirements forsubcontractor/vendor specifica-tions: demonstration of maintain-ability requirement achievement.

Al1 third tier references, tiered to MIL-STO~70, are for guidance and

First Tier (90 of 9b DOcuments)-

MIL-E-85583 Electric Power Generating Channel , Any QPL itern.Variable Input Speed, AlternatingCurrent, 400 Hz, Aircraft; GeneralSpecification for


REFERENCED BY:

MIL-D-8708

MIL-O-8708

information.

MIL-O-8708

Al1 second and third tier.references, tiered to MIL-E-85583, are for guidance and information.


NOJ

TABLE X. Reauired documents and (0rresclondina aDDlicabilitv data (continuedl.



MIL-STD-785 Reliabi11ty Program for Systemsand Equipment Development andProduction

Second Tier

MIL-STD-105 Sampling Procedures and Tables for,Inspectionby Attributes

Second and Third Tier$

The remaining second and third tier references, tiered

First Tier (92 of 9b Documental

MIL-STD-471 Maintainabi1ity Verification/Demonstration/Evaluation

Second and Third Tier

Reliability demonstration; data MIL-O-8708collection requirements (5.3/5.4).

Sampling - visual and mechanical, MIL-STD-785insertion and withdrawal force,torque and life test.

x>~

to MIL-STD-785, are for guidance and information. ~ ~

Collection of maintainabiliduring all phases of testirdemonstration.

Al1 second and third tier references, tiered to MIL-5TD-471 , are for guidance and nformation.


TABLE X. Reauired documents and corresDondinq aopIicability data (continuedl.

Nmm


First Tier (93 of 9b OocumentQ

MIL-STD-1333 Alrcrew Station Geometry forHi1itary Aircraft

Second Tier

t41L-S-18471 System, Aircrew Automated Escape,Ejection Seat Type: General,Specification for

MIL-STD-1472 Human Engineering Design Criteriafor t4i1itary Systems, Equipment,and Facilities

I’IIL-STO-203 Aircrew Station Controls and Ois-plays, Assignment, Locations, andActuation of; for Fixed Ming Air-craft

MIL-STO-250 Aircrew Station Controls and Ois-plays for Rotary Wing Aircraft

APPLICABILITY:

General requirements.

Ejection seat design and seatcomponents.

Anthropometry.

Reach zone requirements forcontrols; location and actuationof controls.

Reach zone requirements forcontrols; location and actuation

REFERENCED BY:

MIL-O-8708

MIL-STO-1333

MIL-STD-1333

of controls.

The remaining second tier references, tiered to MIL-STD-1333, are for guidance and information.

Third Tier

MIL-STO-1472 Human Engineering Oesign Criteria Crew member accommodations.for Mi1itary Systems, Equipmentand Facilities

MIL-S-18471


lABLk X. ReCWl red documents ano corresDonalna am IicablIltv data (conrlnueol.

DOCUMENT NUMBER: DOCUMENT TITLE: APPLICABILITY:

FIIL-F-87242 F1ight Control System, General Requirements except for lubrication(Replaces Specification for and salt spray requirements.MIL-A-8064)

MIL-H-19089 Harnesses, Integrated Parachute Torso restraint.

MIL-I-23659 Initiators, Electrical, General Requirements and qua]ity assurance.Design Specification for

MIL-STD-1385 Preclusion of Ordnance Hazards in Protection from electromagneticElectromagnetic Fields; General radiation.Requirements for

hiIL-P-6645 Parachutes, Personnel, General Parachute requirements.Specification for

hiIL-C-81774 Control Panel, Aircraft, General Reauirements for location andRequirements actuation of controls.

REFERENCED BY:

MIL-S-18471

MIL-S-18471

MIL-S-18471

MIL-S-

MIL-S-

HIL-STD-203MIL-STD-250

First Tter (94 of 9b Documents}

8471

B471

The remaining third tier references, tiered to MIL-STD-1333, are for guidance and information.

NAVAIRINST 3710.9

Second Tier

All second and

Anthropometric Accommodation in Contractor pilots anthropometricNaval Aircraft restrictions.

third tier references, tiered to NAVAIRINST 3710.9, are for guidance and

MIL-D-8708

information.

>wvmz0wxn


TABLE X. @ired do~ and corre~icabilitv data (continued).

DOCUMENT NUMBER : DOCUMENT TITLE: APPLICABILITY:

first Tier (95 of 96 Docum~

OPNAVINST 4790.2 Naval Aviation Maintenance Program Guidance and information.

Seco d and Thi d Tiers.n r

All second and third tier references, tiered to OPNAVINST 4790.2, are for guidance

first Tier (96 of 96 llo~

MI L-STD-461 Electromagnetic Emission and Part I General requirements

REFERENCED BY:

MIL-D-8708

and information.

MIL-D-8708Susceptibility Requirements for and Part 2 Eaui!Jmintand svstemsthe Control O? Electromagnet c installed abroad aircraft l”includlngInterference associated ground support e


All second and third tier

(Class Al)

references, tiered to MIL-STD-461 , are for guidance and

uipment


MIL-D-8708C(AS)

INDEX

ParaaraDh

Acceleration and decelerate ens ................... 3.4.4 .2.2.3Acceleration characteri sties ..................... 3.4.4 .2.1.3Acceptance and witnessing procedures ............. 3.1 .5.5Accessory equipment .............................. 3.8.6Accessory equipment demonstration report. ........ 3.11.3.58Accessory equipment demonstration test plan ...... 3.11.3.57Accuracy ......................................... 3.5.4.2.7ACLS closed loop flight demonstrate on ............ 3.6.5 .5.3.5ACLS functional check flight .................... 3.6.5 .5.3.3ACLS ground demonstrate on ........................ 3.6.5 .5.3.2ACLS open loop flight demonstrate on .............. 3.6.5 .5.3.4ACLS simulation demonstrate on .................... 3.6.5 .5.3.1Acoustical noise level ........................... 3.7.7 .2.7Acoustic signature ............................... 3.10.1.3Acquisition requirements ......................... 6.2Addenda to this specificati on .................... 1.4Aerodynamic conferences ..........................3.1.2.3Aerodynamic demonstration tests .................. 3.3Aerodynamic demonstration test plan .............. 3.11.3.17Aeroelastic stability flight tests ............... 3.2.4 .2.1.1.1Aeroacoustic ground and flight tests ............. 3.2.4 .2.1.1.3Afterburner operation ............................ 3.4.4 .2.2.6Alr starts ....................................... 3.4.4 .2.2.9Air-to-ground rockets ............................ 3.5.4 .2.2.1Air-to-air refuel ino system ...................... 3.7.8.2AircraftAircraft

AircraftAircraftAircraftAirframeAltitudeAngle of

chanaes ...~..~.......................... 3.8.2configurate on ........................... 3.2.2

3.3.23.4.23.5.23.6.2

flight control systems .................. 3.6.5 .3.4instrumentati on ......................... 3.6.3weapon system accuracy report ........... 3.11.3.33movable components and subsystems ....... 3.7.8.8idle scheduje at low airspe~ds .......... 3.4.4 .2.2.2attack systems .......................... 3.7.6.7

Antennas ......................................... 3.7.4 .1.5Anti-g protective system ......................... 3.7.7 .2.8Anti-icing and de-icing .......................... 3.4.4 .2.2.8Appendl xA Contractor Demonstration Requirements for

Navy Development Tests ..................B Schedule of Oates for Submission of Repor”

and for Conferences .....................C Streamlining Information .................

Applicabi lity ................................Applicabl e documents ..........................

. ..-5...-. ..-. . . 1.3... 2.

20.Application ...................................... 10.2Approach Power Compensator System Tests (APCS). .. 3.6.5.5.2APCS flight tests ................................ 3.6.5 .5.2.2

E!i9e

5755109611111175838380838091

17;1i301072629585872939614305266767977109

...... 94

;;859158

126-131

132-143144-270

12

126, 132, 1441448080

271


MIL-D-8708C(AS)

INOEX

Paraqra@

APCS ground tests ................................ 3.6.5 .5.2.1Approach speeds.................................. 3.6.5.4.3Armament build-up program ........................ 3.5.4.1Armament control system .................Armament demonstration report. ..........Armament ground support equipment. . ...Armament system densenstration...........Armament system demonstration test Dlan.

. . . . . 3.5.4.2.6

. .. .. 3.11.3.34

....... 3.5.4.2.8

........ 3.5

. . . . . . . . 3.11.3.30Armament s~stem flight and ground demons rations. 3.S.4.2Armament system test ............................. 3.5.1Arrest ing........................................ 3.6.5.4Arresting configurations ......................... 3.6.5 .4.1Arrest ing hook damping ........................... 3.6.5 .4.2Artificial loss-of-control prevention system. .... 3.3.4 .2.7Artificial loss-of-control warning ............... 3.3.4 .2.6Artificial stall warning ......................... 3.3.4 .2.4Attitude indicating systems (remote)............. 3.7.6.4Automated Flight Control System (AFCS) ........... 3.6.5 .5.1Automatic Carrier Landing System (ACES).......... 3.6.5.5.3Automatic llfe raft release system ............... 3.7.7.2.12Aviation life support systems .................... 3.7.7 .2.9Avionic system demons tration ..................... 3.7.4Avionic system demonstration reports ............. 3.11.3.40Avionic system demonstration test plans .......... 3.11.3.39Avionics demonstration conference ................ 3.1.2.4Ballistic and warhead tolerance demonstration. ... 3.10.2.1Battery discharge ................................ 3.7.5 .1.9Baseline stability and control tests ............. 3.3.4 .3.6Bi-Weekly Summary- Reports. ...Brakes .......................Build-up test program .,......Captive carry tests ..........Cargo carrying and handling..Carrier suitability demonstraCarrier suitability demonstraCarrier suitability demonstra

. . . . . . . . . . . . . . . . . . . 3.11 .3.5

................... 3.7.8 .8.2.3

................... 3.4.4.1

...... ............ 3.5.4 .2.3.1

................... 3.8.6.2ion................ 3.6ion report ......... 3.11.3.38ion test plan

and schedule ................................. . 3.11.3.35Carrier suitability demonstration tests .......... 3.2.4 .2.2.4Carrier suitability tests ........................ 3.6.1hhpUlti rig . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.6.5.3

Catapult accessories ............................. 3.6.5 .3.1Catapult spotting (prior to tensioning ).......... 3.6.5.3.2Center of gravity positions ...................... 3.6.2.1Change sfrom previous issue... ...................6.9Chase aircraft ................................... 3.1 .4.4Check calibrations ............................... 3.1.5.3Class ification ................................... 3.3.2.2Cockpit instrumentation and layout ............... 3.3.3.1Combat survivability demonstration test plan ..... 3.11.3.62Combat survivabi 1ity demonstration test

report ......................................... 3.11.3.63

272

!wL!2

808067

1:;7665108706579808037363689808092

:1109109

1049552729776109

1092976787878

1;:

1:3031111

111


MIL-D-8708C(AS)

INDEX

ParaaraDh

Combination of power plants ...................... 3.4.4 .2.3.53.4.4 .2.4.4

Compass systems ..................................3.7.6.3Complete ngthe CDRL .............................. 6.3.1Compressor inlet and turbine outlet

pressure survey ................................ 3.4.4.1.3Compressor inlet and turbine outlet pressure

survey report .................................. 3.11.3.27Condensation ..................................... 3.7.4.1.2Casferences ...................................... 50.Configuration changes ............................ 3.6.5.2Configuration for catapulting .................... 3.6.5 .3.2.1Constant Mach number climbs ...................... 3.4.4 .2.2.1Contamination ..................................... 3.7.7 .2.1Contractor demons tration ......................... 40.1Contractor demonstration requirements ............ 3.2.4

Contractor’s flight operations. ..Control lability ..................

3.3.43.4.43.5.440.

.............. 3.1.6

............... 3.6.5.3.3Control and performance character stic$. ......... 3.6.5.6.1COntrOl ]ever tests .............................. 3.4.4 .2.5.5Conventional stores .............................. 3.5.4 .2.4.1Countermeasures demons tration .................... 3.10.1.6Crew station and cabin conditioni rig ............. 3.7.7.2Crew systems and human enalneerina demonstration. 3.7.7Crew s~stems and human en~ineerin~ demonstration

test plan ...................................... 3.11.3.47Crew systems and human engineering demonstration

report ......................................... 3.11.3.48Oaily Flight Reports ............................. 3.11 .3.4Data requirements ................................ 6.3Definition s...................................... 6.4Demons tration .................................... 3.6.5.1Demonstration of engine characteristics during

ground operation ............................... 3.4.4.2.1Demonstration of engine characteristics

In flight ...................................... 3.4.4.2.2Demonstration instrumentation report ............. 3.11 .3.3.1Demonstration planning and progress report ....... 3.11 .3.2Demasstratl on program plan..... .................. 3.11 .3.1Demonstration report ............................. 3.11 .3.6Demcwsstration test requirements .................. 3.6.5Development tests ................................ 30.1Deviations ....................................... 1.5Documents ........................................ 20.1Drag Measurements ................................ 3.3.4 .2.1.1Droppable stores ................................. 3.5.4 .2.4DT-IIA ........................................... 30.3.1DT-IIB and subsequent evaluations, ............... 30.3.2

273

&c!

606489112

53

108841317879

:;129

::

::129117983657398

::

110

11010311211277

54

56102

R10477126

11443673126128


MIL-D-8708C(AS)

INDEX

Parac!raDh

Electrical bonding ............................... 3.7.5.1.7Electrical power ................................. 3.7.5 .1.3Electrical system ................................ 3.7.5Electrical system demonstration report ........... 3.11.3.44Electrical system demonstration test plan ........ 3.11.3.43Electromagnetic Compatibi 1ity (EMC)demonstrate on test plan ........................ 3.11.3.41

Electromagnetic Compatibi 1ity (EMC)demonstration report ........................... 3.11.3.42

Emergency electrical power ....................... 3.7.5 .1.4Emergency recovery device ........................ 3.3.2.4Emission Control (EMCON) ......................... 3.7.4.1.16Emergency manual egress system ................... 3.7.7.2.11Emergency protection ............................. 3.4.4 .2.2.5Engine and flight instrument transmittermountings, temperature, and vibrationlimit tests .................................... 3.7.6.6

Engine fuel feed ................................. 3.4.4 .2.6.3Engine installation temperature survey ........... 3.4.4.1.2Engine installation vibration test plan .......... 3.11.3.24Engine operating characteri sties ................. 3.3.4.3.3Engine operation during tests .................... 3.2.4.1.4Engine performance monitoring system ............. 3.4.4.2.2.11Engine power parameter systems ................... 3.7.6.5Engine power output tests ........................ 3.4.4.2.3Engine stall checks .............................. 3.4.4 .2.2.4Engine temperature survey report ................. 3.11.3.26Engine vibration survey ..........................3.4.4.1.1Engine vibration survey report ................... 3.11.3.25Environmental factors evaluation ................. 3.5.4 .1.2Exhaust gas ingestion ............................ 3.6.5 .6.2External power protection ........................ 3.7.5.1.8Facilities for carrier suitability tests ......... 3.6.4Feathering pitch tests ........................... 3.4.4 .2.5.3Field emergency arresting gear ................... 3.2.4 .2.2.3Field Carrier Landing Practice (FCLP) tests ...... 3.2.4 .2.2.2Field taxi , field takeoff and field

landing tests ................................. 3.2.4 .2.2.1Fighter, trainer and light attack aircraft ....... 3.5.4 .2.1.2Figure 1 On-center and off-center spotting fornose gear launch aircraft.. .................... -

Fire warning, bleed air leak detection, andfire extinguishing systems and fire/explosionSuppression systems ............................ 3.7.8.3

Flame damping .................................... 3.4.4.2.2.10Flight check ..................................... 3.7.8 .1.2Flight control system demonstration report. ...... 3.11.3.37Flight control systems ........................... 3.6.5.5Flight demonstration tests ....................... 3.3.4.2Flight equipment ................................. 3.1 .6.4Flight functional tests .......................... 3.5.4.1.3Flight monitoring ................................ 3.1.4Flight simulation program ........................ 3.3.4 .1.1

274

m9E

8888

1:;109

109

1098830879158

896550108502259895958108

1::

642929

2970

78

93599210980361469

3:


MIL-D-8708C(AS)

I NOEX

Pa raaraI)h

Flight test build-up program ..................... 3.2.4.13.3.4.1

Flight test program .............................. 3.3.1””..-.

Flight test vehicle .............................. 3.3.2.1Flight tests for load survey of airframe

Structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.2.4 .1.1Flight test instrumentation ...................... 3.2.3

3.3.33.4,33.5.3

Flight test verification program ................. 3.3.4 .1.2Fluid anti-ice systems .........,.................3.7.8.5.3Flying qualities demonstration conference ........ 3.1 .2.3.4Flying qualities demonstration report ............ 3.11.3.18Formal structural flight and grounddemonstration s................................. 3.2.4.2

Format and general requirements .................. 3.11.1Free-flight missile launches ..................... 3.5.4 .2.3.2Fueling anddefuel ing............................ 3.4.4 .2.6.4Fuel dumping .....................................3.4.4.2.6.1Fuel nozzle ground ing............................ 3.7.5 .I.1o

Fuel system densmstrati on ........................ 3.4.4 .2.6Fuel transfer system ............................. 3.4.4 .2.6.5Fuel quantity gage systems ....................... 3.7.6.2Fuel venting .....................................3.4.4.2.6.2Gaseous and liquid oxygen ........................ 3.7.7 .2.4Government documents ............................. 2.1Gross weights .................................... 3.2.2.1Gross weight and e.g. posit ions .................. 3.3.2.3Gross weight and loading conditions .............. 3.6.2.2Ground check ..................................... 3.7.8.1.1Ground functional tests .......................... 3.5.4 .1.1Ground surveil lance .............................. 3.1.4.3Guaranteed performance report .................... 3.11.3.21Guided missile demonstration requirements ........ 3.5.4.2.3Gun demonstration requirements ................... 3.5.4 .2.1Gunfire vibration and aeroacoustic environment ... 3.5.4 .2.1.3Gunfire vibration and aeroacousti c environ-

meritmeasurement report ........................ 3.11.3.31Hardness to directed energy and other

specified weapons demon stration ................ 3.1O.2.5Hazards of Electromagnetic Radiation to

Fuel (HERF) .................................... 3.7.4.1.13Hazards of Electromagnetic Radiation toOrdnance (HERO) ................................ 3.7.4 .1.12

Hazards of Electromagnet c Radiation toPersonnel (HARP) ............................... 3.7.4.1.11

Hazards of High-Powered Microwaves (HPM) ......... 3.7.4.1.15Hazards of lasers................................ 3.7.4.1.14Heavy attack and patrol aircraft ................. 3.5.4 .2.1.1High AOA and spin planning

conferences .................................... 3.1.2.3.2High AOA flight test variable s................... 3.3.4 .2.2High AOA/spin demonstration report ............... 3.11 .3.19.2

275

m17323030

1715315266

9108

;;71

108

98

86

86

86878670

836107


MIL-D-8708C(AS)

INDEX

Paraara~h

High AOA/spin demonstration schedule report ...... 3.11.3.19H\gh pitch tests ................................. 3.4.4 .2.5.2Hoisting sling ...................................3.8.6.4Human engineering and crew station demon-

stration ....................................... 3.7.7.1Hunting and surging .............................. 3.4.~.2.s.7Hydraulic and pneumatic systems .................. 3.7.8.4Ice protection systems ........................... 3.7.8.5Icing survey report .............................. 3.11.3.52Iclngsurvey test plan ........................... 3.11.3.51Imaging system demon stratlon ..................... 3.7.8.1Infrared radiation ............................... 3.10.I.2Inspection ....................................... 40.3Installation ..................................... 3.7.4.1Installation, calibration, and maintenance ....... 3.1 .5.2Installed systems demons tration .................. 3.7Installed systems and equipment .................. 3.7.1Instrumentati on .................................. 3.1.5Instrumentation planning conferences ............. 3.1.2.1Instrumentation reports .......................... 3.11 .3.3Instrument system ................................ 3.7.6Instrument systems derrmstratlon plan ............ 3.11.3.45Instrument systems demonstration report. ......... 3.11.3.46Intended use ..................................... 6.1Intentional and unintentional emissions .......... 3.1O.1.4Interface tests .................................. 3.7.4 .I.4Intrasystem Electromagnetic Compatibility (EMC)and Electromagnetic Interference (EMI). ...’.....3.7.4 .1.7

Intersystem Electromagnetic Compatibility(Electromagnetic Vulnerability (EMV) ........... 3.7.4.1.8

Inverted fuel/oil system ......................... 3.3.2.5Jet blast deflector acoustic and thermal

environment report ...................Jet blast deflector acoustic and therms’

environment test .....................Jettison requirements ..................Landing gear ...........................Llghtlng ...............................

. . . . . . . . . 3.11.3.36

. . . . . . . . . 3.6.5.3.6

......... 3.5.4 .2.3.3

......... 3.7.8 .8.2

......... 3.7.5 .1.6Lightning ........................................ 3.7.4 .I.17Location of demonstration program ................ 3.1 .1.1Lowpltch tests ...........”...~................... 3.4.4 .2.5.1Maintenance ...................................... 3.8.3. ]Maximum control author ity........................ 3.2.4 .1.5.2Military power runs .............................. 3.4.4 .2.4Miscellaneous ............................Miscellaneous installed systems ..........Miscellaneous installed systems demonstra’

test plan ..............................Miscellaneous Installed systems

report .................................Missile vibration and aeroacoustic

. . . . . . . 3.5.4 .2.9

....... 3.7.8ion....... 3.11.3.49

....... 3.11.3.50

environment measurement report ................. 3.11.3.32Missile v~bration and aeroacoustic

environment measurement tests .................. 3.5.4 .2.3.4

276

Mgg

1076497

896594

17;11092

lx

84

8;8497

102

1!:1101129884

86

8631

109

7973958887664

;:607692

110

110

109

73


MIL-D-8708C(AS)

INDEX

ParaclraDh

Motion picture camera and video tape coverage. ... 3.1 .4.1Natural loss-of-control warning .................. 3.3.4.2.5Natural stall warning ............................ 3.3.4.2.3Navy development tests ........................... 30.Noise level measurements ......................... 3.4.4 .2.1.4Non-Government publications ...................... 2.2Non-pressurized aircraft ......................... 3.7.7 .2.3Normal flight limits ............................. 3.1 .6.3Nose gear steering ............................... 3.7.8 .8.2.2Notes ............................................ 6.Nuclear, Biological, and Chemical (NBC)

warfare suitability demon stration .............. 3.10.2.4Nuclear Electromagnetic Pulse (NEMP) ............. 3.7.4.1.10Nuclear hardness and hardness assurance

demonstrate on .................................. 3.10.2.2Nuclear weapons requirements ..................... 3.5.4.2.5Objectives ....................................... 30.2Onboard cameras .................................. 3.3.3.2On-Board Oxygen Generating System (OBOGS). ....... 3.7.7 .2.5Operation of appurtenances ....................... 3.2.4.1.6Operation of flight control systems .............. 3.2.4.1.5Operations Security (OPSEC) ...................... 3.1.3Operation with gun, rocket and missile firings ... 3.4.4 .2.2.7Optical apertures ................................ 3.7.4.1.9Order of precedence .............................. 2.3Other Government documents, drawings, and

publications ................................... 2.1.2Out-of-control recovery procedures. .............. 3.3.4.3.1Packaging ........................................ 5.Parachute and survival equipment assembly. ....... 3.7.7 .2.1OPerformance data reduction procedures

conference ..................................... 3.1.2.3.1Performance data-reduction report. ............... 3.11.3.20Performance demonstration ........................ 3.7.5.1Performance demonstration planning conferences. .. 3.1 .2.3.3Performance demonstration report ................. 3.11.3.22Performance tests ................................ 3.3.4 .2,1Pitot and pitot static systems (altimeterand airspeed indicator ).... .................... 3.7.6.1

Planning conferences ............................. 3.1.2Pneumatic anti-ice systems ....................... 3.7.8 .5.2Post DT-II conferences ...........................50.2Precipitation static............................. 3.7.4.1.18Pre-DT-II conferences ............................ 50.1Pre-DT-11 engineering data ....................... 40.2Pre-engineering report ........................... 3.11 .3.7Prerequisites for first flight ................... 3.1 .6.1Pressurized aircraft ............................. 3.7.7 .2.2Pre-structural demonstration report .............. 3.11.3.12Prime mover capacity ............................. 3.7.5.1.2Program planning information ..................... 3.1Propeller demons tration .......................... 3.4.4 .2.5

277

3:36126566

987512631

;;22

5:866

5

1:;

10836

897

941318713112910611901068B6

64


MIL-D-8708C(AS)

INDEX

Propel 1erPropellerPropel 1er

ParaclraDh

driven aircraft ........................ 3.4.3.4vibration survey ....................... 3.4.4 .1.4vibration survey report ................ 3.11.3.29

Proposed flight envelopes~ ........................ 40.4Propulsion system demonstration .................. 3.4Propulsion system demonstration report ........... 3.11.3.28Propulsion system demonstration test plan. ....... 3.11.3.23Propulsion system ground and flight

demonstrations ................................. 3.4.4.2Propulsion system tests .......................... 3.4.1Protection ....................................... 3.7.5 .1.5Purpose .......................................... 1.2Qualitative spin description ..................... 3.3.4.3.7Quality Assurance Provisions ..................... 4.R&Mdata and review .............................. 3.8.4Radar and infrared equipments .................... 3.7.4.1.6Radar signature measurement ...................... 3.10.1.1Rain removal systems ............................. 3.7.8.6Ram-jet and pulse-jet engines .................... 3.4.4 .2.3.4Ram-jet, pulse-jet, and rocket engines ........... 3.4.4 .2.4.3Re-calibrations .................................. 3.1.5.4Recovery characteri sties ......................... 3.3.4.3.4Release for flight and operating limits .......... 3.1 .6.2Release of stores in flight ...................... 3.5.4 .2.4.1.1Reliability and maintainabi lity .................. 3.8.1Reliability and maintainability demasstration. ... 3.8Reliability and maintainability demonstration

report ......................................... 3.11.3.54Reliabi1ity and maintainabi 1ity demonstration

test plan ...................................... 3.11.3.53Reports .......................................... 3.11Required reports ................................. 3.11.3Retraction and recension ......................... 3.7.8 .8.2.1Requirements ..................................... 3.Requirement prior to TECHEVAL .................... 40.5Requirements prior to 1ST andlor ACLS/ST. ........ 40.6Reverse pitch tests .............................. 3.4.4 .2.5.4Rocket demonstration requirements ................ 3.5.4 .2.2Rocket engines ..........’......................... 3“.4.4.2.3.3Rocket, ram-jet and pulse-jet engines ............ 3.4.3.3Safety assessment report ......................... 3.11 3.61Scope ............................................ 1.

1.110.10.1

Scape and correlative provision s................. 3.1.’Scope of tests ................................... 30.3Service 1ife effects on control surfaces. tabs.

andwingfal do ........................~........ 3.2.4 .2.1.1.4

278

PJg!

525310812950108108

5350881

50112968597946063105012739595

110

1109899956

12913065725952111

1i

126, 132, 144126, 132, 144

6126

29


MIL-D-8708C(AS)

INDEX

ParaaraDh

Special Flight Test Instrumentation(SFTI) Excess Equipment Report ................. 3.11 .3.3.4

Special Flight Test Instrumentation(SFTI) Inventory and Status Report ............. 3.11 .3.3.3

Special Flight Test Instrumentation(SFTI) Requisition and Technical Data Report ... 3.11 .3.3.5

Special vulnerabi 1ity equipment demon-stratiens ...................................... 3.10.2.3

Specifications, standards, and handbooks ......... 2.1.1Specific test requirements ....................... 3.3.4.3Spin demonstration schedule report ............... 3.11 .3.19.1Spin recovery-class I and IV aircraft ............ 3.3.4.3.2Starting characteri sties ......................... 3.4.4 .2.1.1Steady state characteri sties ..................... 3.4.4 .2.1.2Steam ingestion tests demonstrate on .............. 3.6.5.3.5Store release structural load survey ............. 3.2.4.1.3Streaml ining ..................................... 2.4

6.7Structural conferences ........................... 3.1 .2.2Structural demons tration ......................... 3.2Structural demonstrations report ................. 3.11.3.13Structural Demonstration Test Plan ............... 3.11 .3.8Structural dynamic flight demons tration .......... 3.2.4 .2.1.1Structural dynamic flight demonstration

planning conference ........................... 3.1 .2.2.5Structural dynamic flight demonstration

report s........................................ 3.11.3.14Structural flight and ground demonstrations. ..... 3.2.4.2Structural flight demons tration .................. 3.2.4.2.1Structural flight demonstration planning

conference .................................... 3.1.2.2.3Structural flight limitations tests .............. 3.2.4.1.2Structural flight limitations report ............ 3.11.3.11Structural flight load survey planning

conference .................................... 3.1.2.2.2Structural flight loads instrumentation. ......... 3.2.3.1Structural flight loads survey report ............ 3.11.3.10Structural flight test anomaly and

failure report ................................. 3.11.3.15Structural ground loads and carrier suitabi1ity

demonstration planning conference .............. 3.1 .2.2.4Structural ground loads and carrier

suitability demonstration report ............... 3.11.3.16Structural instrumentation calibration ........... 3.2.3.3Structural instrumentation planning conferences. . 3.1 .2.2.1Structural Instrumentation Report ................ 3.11 .3.3.2Structural pre-flight load survey report. ........ 3.11 .3.9Subject term (keyword) listing .................. 6.6Submiss ion of reports ............................ 3.11.2Support demons tration ............................ 3.8.5

103

103

103

98

3$10737545579226

125

li10610626

8

717

106

715106

107

8

107167

103106124

;:

279


MIL-D-8708C(AS)

INOEX

ParaaraDh

Supportability demonstrate on. .................... 3.8.5.1Support demonstration report ..................... 3.11.3.56Support demonstration test plan .................. 3.11.3.55Susceptibility demonstrate on ..................... 3.10. ISymbols, abbreviations, and acronyms ............. 6.5Synchronization and synchrophas ing............... 3.4.4 .2.5.6Systems configuration ............................ 3.7.2System safety demonstrate on...................... 3.gSystem safety demonstration report. .............. 3.11 .3.61JSystem safety demonstration test plan. ........... 3.11.3.59System survivabi lity/vulnerabi 1ity demon-

strati on . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3.10Tables

Conference schedule....................... -Conference with no fixed convening date.. . -Required documents and correspondingapplicabi lity data ..................... -

of report submission/conferences convening

Flight tests for load survey structures. ... -:: Structural flight limitations test......... -IC Structural demonstration tests. ............ -11A Field landing tests ....................... -IIB Field carrier landing practice tests. ..... -111A High angle of attack build-up tests ....... -IIIB Flying qualities demonstration tests ...... -IIIC High angle of attack demonstration tests. . -IV Spin mode modifiers ....................... -v Arrested landing tests .................... -VI Reports schedule and data iterndescription -VII Reports with no fixed submission date. .... -VIIIIXx

Tablesdates .......................................... 30.

Tailoring ........................................ 6.8Taxi, takeoff and landing tests .................. 3.2.4 .2.2Taxi , takeoff and landing test instrumentation. .. 3.2.3.2TECHEVAL ......................................... 30.3.3Telemetry coverage ............................... 3.1 .4.2Temperature. ..................................... 3.7.4.1.1Temperature and vioration ........................ 3.7.5 .1.ITEMPEST .......................................... 3.7.4.1.19Testability demons tration ........................ 3.8. ].1Test flights ..................................... 3.8.3Test instrumentation ............................. 3.1.5.1

3.7.3Tests and demonstrate on....... ................... 3.z.1Thermal anti-ice systems ......................... 3.7.E.5. IThermal protective system ........................ 3.7.7 .2.6Tie-down, jacking, and towing .................... 3.8.6.3Training maneuvers ............................... 3.3.4 .3.5Transmission operation demons tration. ............ 3.4.4 .2.5.8Trim ............................................. 3.2.4 .1.5.1Turbojet/turbofan ................................ 3.4.4 .2.1.4.2

280

PJiQ

9611111197120658497111111

97

1819, 20, 21

24, 2527

33, 34, :;38-48

49

81, ii133-139

140, 141142143

145-270

1321252915

1289

:;87

::

8;1494919750652356


MIL-D-8708C(AS)

INDEX

ParaaraDh

Turbojet/turbofan engines ........................ 3.4.3.1

Turboprop/turboshaft. ...............Turboprop and turboshaft engines. ...

Vertical /Short Take-Off and Landingaircraft ..........................

Vibration and shock load ............Vibration fliaht tests ...............

. . . . .

. . . . .

STOL).....

. . . . . . .

. . . . . . .

3.4.4 .2.3.23.4.4 .2.4.23.4.4 .2.1.4.13.4.4 .2.3.13.4.4 .2.4.13.4.3.2

3.6.5.6. . . . . . . . . . . . 3.7.4.1.3............ 3.2.4 .2.1.1.2

Visible, UV, ~nd other short wavelengthphenomena ...................................... 3.10.1.5

Vulnerability reduction demonstration ............ 3.10.2Watertightnes s................................... 3.7.8.7Wave-of f capability .............................. 3.6.5 .4.4Winches and hoists ............................... 3.8.6.1Wing folding or sweeping and spreading(ship-based aircraft) .......................... 3.7.8 .8.1

PJiQ

5259

!5:59

;:

838429

9898948097

95

281


MIL-D-8708C(AS)

Preparing activity:Navy - AS

(Project 151O-NO58)

282


I

STANDARDIZATION DOCUMENT IMPROVEMENT PROPOSAL

INSIRUCT30NS

1. The preparingactivitymustcompleteblocks1,2,3,and 8. Inblock 1. both the document number and revisionlettershouldbegiven.

2. The submitter of this form must complete block~ 4,5,6, and 7.

3. The preparing activity must provide a reply within 30 days from receipt of the form.

NOTE: This form may not be used to request copies of documentt, nor to reque!t waivers, or clarification ofrequirements on current contracts. Comments wbmitted on this form do not constitute or imply authorization towaive any portion of the referenced document(s) or to amend contractual requirements.

‘ ‘:., 1. DOCUMIMf NUM#t#lJu;Ec:o:M:M,E~;D;~;<:HAg:GE:2

2. 00 CUMCNI OAIC (7 YMMOO)

.:. MIL-D-8708 C(AS)” 12 August 1991DOCUMENT TITLE

DEMONSTRATION: AIRCRAFT WEAPON SYSTEMS , GENERAL SPECIFICATION FORNATURE OF cnAMG~ Ildenti& p.r.yanh number .nd kwl.d. proposed rewrite, If p.wibk AN.ch extr. shrrO .1 needed.)

REASON FOR RECOMMENDATION

I........... —..

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D Form 1426, Ocl 89 FTWIOUI editiom .re obcokte. !*V7W

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